NACA 63(3)-018 (naca633018-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(3)-018 (naca633018-il) Reynolds number: 100,000 Max Cl/Cd: 36.37 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca633018-il-100000-n5.txt Download as CSV file: xf-naca633018-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-018
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9417 0.11905 0.11331 -0.0080 1.0000 0.0509
-17.750 -0.9801 0.10798 0.10193 -0.0148 1.0000 0.0511
-17.500 -1.0094 0.09934 0.09298 -0.0197 1.0000 0.0514
-17.250 -1.0072 0.09605 0.08969 -0.0211 1.0000 0.0526
-17.000 -1.0051 0.09287 0.08649 -0.0225 1.0000 0.0538
-16.750 -1.0111 0.08851 0.08200 -0.0246 1.0000 0.0548
-16.500 -1.0187 0.08400 0.07734 -0.0266 1.0000 0.0558
-16.250 -1.0261 0.07964 0.07279 -0.0284 1.0000 0.0568
-16.000 -1.0325 0.07553 0.06847 -0.0299 1.0000 0.0579
-15.750 -1.0375 0.07170 0.06441 -0.0311 1.0000 0.0590
-15.500 -1.0414 0.06814 0.06060 -0.0321 1.0000 0.0601
-15.250 -1.0414 0.06508 0.05733 -0.0327 1.0000 0.0613
-15.000 -1.0272 0.06343 0.05571 -0.0327 1.0000 0.0628
-14.750 -1.0176 0.06147 0.05370 -0.0328 1.0000 0.0641
-14.500 -1.0087 0.05945 0.05160 -0.0330 1.0000 0.0656
-14.250 -1.0001 0.05742 0.04946 -0.0331 1.0000 0.0672
-14.000 -0.9911 0.05545 0.04735 -0.0331 1.0000 0.0690
-13.750 -0.9803 0.05364 0.04538 -0.0331 1.0000 0.0707
-13.500 -0.9662 0.05215 0.04381 -0.0328 1.0000 0.0725
-13.250 -0.9517 0.05079 0.04248 -0.0325 1.0000 0.0742
-13.000 -0.9390 0.04935 0.04102 -0.0323 1.0000 0.0762
-12.750 -0.9266 0.04789 0.03952 -0.0321 1.0000 0.0785
-12.500 -0.9135 0.04651 0.03805 -0.0318 1.0000 0.0811
-12.250 -0.9000 0.04519 0.03666 -0.0314 1.0000 0.0838
-12.000 -0.8890 0.04375 0.03527 -0.0310 1.0000 0.0865
-11.750 -0.8783 0.04229 0.03381 -0.0307 1.0000 0.0896
-11.500 -0.8668 0.04091 0.03240 -0.0303 1.0000 0.0931
-11.250 -0.8559 0.03951 0.03098 -0.0299 1.0000 0.0971
-11.000 -0.8488 0.03784 0.02937 -0.0295 1.0000 0.1016
-10.750 -0.8395 0.03636 0.02787 -0.0290 1.0000 0.1076
-10.500 -0.8329 0.03471 0.02627 -0.0286 1.0000 0.1139
-10.250 -0.8250 0.03318 0.02475 -0.0281 1.0000 0.1222
-10.000 -0.8201 0.03148 0.02314 -0.0275 1.0000 0.1318
-9.750 -0.8147 0.02988 0.02162 -0.0269 1.0000 0.1438
-9.500 -0.8106 0.02827 0.02011 -0.0262 1.0000 0.1593
-9.250 -0.8082 0.02672 0.01870 -0.0252 1.0000 0.1781
-9.000 -0.7931 0.02502 0.01711 -0.0270 0.9456 0.2081
-8.750 -0.7843 0.02359 0.01579 -0.0267 0.9213 0.2405
-8.500 -0.7827 0.02260 0.01490 -0.0241 0.9011 0.2698
-8.250 -0.7800 0.02187 0.01428 -0.0210 0.8854 0.3015
-8.000 -0.7725 0.02131 0.01383 -0.0184 0.8726 0.3350
-7.750 -0.7609 0.02092 0.01351 -0.0161 0.8613 0.3661
-7.500 -0.7458 0.02066 0.01325 -0.0143 0.8505 0.3928
-7.250 -0.7297 0.02045 0.01297 -0.0125 0.8415 0.4163
-7.000 -0.7108 0.02033 0.01283 -0.0111 0.8320 0.4368
-6.750 -0.6910 0.02032 0.01277 -0.0097 0.8240 0.4565
-6.500 -0.6701 0.02035 0.01272 -0.0085 0.8153 0.4752
-6.250 -0.6483 0.02042 0.01272 -0.0073 0.8081 0.4913
-6.000 -0.6248 0.02047 0.01270 -0.0065 0.7999 0.5041
-5.750 -0.6030 0.02039 0.01246 -0.0055 0.7936 0.5155
-5.500 -0.5768 0.02048 0.01252 -0.0051 0.7855 0.5253
-5.250 -0.5520 0.02052 0.01246 -0.0043 0.7792 0.5348
-5.000 -0.5286 0.02044 0.01225 -0.0037 0.7719 0.5450
-4.750 -0.5013 0.02052 0.01230 -0.0033 0.7652 0.5515
-4.500 -0.4768 0.02040 0.01206 -0.0027 0.7595 0.5591
-4.250 -0.4508 0.02032 0.01192 -0.0026 0.7521 0.5654
-4.000 -0.4243 0.02029 0.01182 -0.0021 0.7464 0.5711
-3.750 -0.4007 0.02006 0.01144 -0.0018 0.7400 0.5789
-3.500 -0.3726 0.02010 0.01147 -0.0017 0.7336 0.5832
-3.250 -0.3464 0.02001 0.01130 -0.0013 0.7286 0.5888
-3.000 -0.3216 0.01982 0.01101 -0.0012 0.7219 0.5957
-2.750 -0.2939 0.01983 0.01100 -0.0011 0.7159 0.5997
-2.500 -0.2674 0.01975 0.01084 -0.0007 0.7113 0.6050
-2.250 -0.2422 0.01959 0.01060 -0.0008 0.7047 0.6118
-2.000 -0.2145 0.01959 0.01061 -0.0006 0.6990 0.6155
-1.750 -0.1875 0.01953 0.01048 -0.0004 0.6946 0.6205
-1.500 -0.1618 0.01943 0.01032 -0.0005 0.6881 0.6271
-1.250 -0.1344 0.01942 0.01032 -0.0004 0.6826 0.6311
-1.000 -0.1072 0.01938 0.01024 -0.0001 0.6783 0.6356
-0.750 -0.0809 0.01934 0.01019 -0.0002 0.6721 0.6418
-0.500 -0.0540 0.01932 0.01016 -0.0002 0.6666 0.6466
-0.250 -0.0266 0.01931 0.01013 0.0000 0.6624 0.6510
0.000 0.0000 0.01932 0.01014 0.0000 0.6567 0.6567
0.250 0.0266 0.01931 0.01013 0.0000 0.6510 0.6624
0.500 0.0540 0.01932 0.01016 0.0002 0.6466 0.6666
0.750 0.0809 0.01934 0.01019 0.0002 0.6417 0.6721
1.000 0.1072 0.01938 0.01024 0.0001 0.6356 0.6783
1.250 0.1344 0.01942 0.01032 0.0004 0.6311 0.6826
1.500 0.1618 0.01943 0.01032 0.0005 0.6270 0.6881
1.750 0.1875 0.01953 0.01048 0.0004 0.6205 0.6946
2.000 0.2145 0.01959 0.01061 0.0006 0.6155 0.6990
2.250 0.2422 0.01959 0.01060 0.0008 0.6118 0.7047
2.500 0.2674 0.01975 0.01084 0.0007 0.6050 0.7113
2.750 0.2939 0.01983 0.01100 0.0011 0.5997 0.7159
3.000 0.3216 0.01982 0.01101 0.0012 0.5957 0.7219
3.250 0.3465 0.02001 0.01130 0.0013 0.5888 0.7286
3.500 0.3726 0.02010 0.01147 0.0017 0.5832 0.7336
3.750 0.4007 0.02006 0.01144 0.0018 0.5789 0.7400
4.000 0.4243 0.02030 0.01182 0.0021 0.5711 0.7464
4.250 0.4508 0.02032 0.01191 0.0026 0.5654 0.7521
4.500 0.4769 0.02040 0.01206 0.0027 0.5591 0.7595
4.750 0.5013 0.02052 0.01230 0.0033 0.5515 0.7652
5.000 0.5286 0.02044 0.01225 0.0037 0.5450 0.7719
5.250 0.5520 0.02052 0.01246 0.0043 0.5348 0.7792
5.500 0.5768 0.02048 0.01251 0.0051 0.5253 0.7854
5.750 0.6030 0.02039 0.01246 0.0054 0.5155 0.7936
6.000 0.6249 0.02047 0.01270 0.0065 0.5041 0.7999
6.250 0.6484 0.02042 0.01272 0.0073 0.4913 0.8081
6.500 0.6702 0.02035 0.01272 0.0085 0.4753 0.8153
6.750 0.6910 0.02032 0.01276 0.0097 0.4566 0.8240
7.000 0.7109 0.02033 0.01283 0.0111 0.4369 0.8320
7.250 0.7297 0.02044 0.01297 0.0125 0.4163 0.8416
7.500 0.7458 0.02066 0.01325 0.0143 0.3925 0.8505
7.750 0.7609 0.02092 0.01351 0.0161 0.3657 0.8613
8.000 0.7726 0.02130 0.01382 0.0184 0.3349 0.8726
8.250 0.7801 0.02187 0.01428 0.0210 0.3013 0.8853
8.500 0.7830 0.02260 0.01490 0.0241 0.2699 0.9011
8.750 0.7845 0.02359 0.01579 0.0267 0.2403 0.9213
9.000 0.7935 0.02501 0.01710 0.0269 0.2083 0.9456
9.250 0.8085 0.02671 0.01869 0.0252 0.1781 1.0000
9.500 0.8111 0.02826 0.02010 0.0261 0.1593 1.0000
9.750 0.8154 0.02985 0.02159 0.0268 0.1440 1.0000
10.000 0.8207 0.03147 0.02313 0.0274 0.1318 1.0000
10.250 0.8257 0.03316 0.02473 0.0280 0.1224 1.0000
10.500 0.8336 0.03469 0.02624 0.0285 0.1139 1.0000
10.750 0.8402 0.03634 0.02785 0.0290 0.1076 1.0000
11.000 0.8496 0.03782 0.02935 0.0294 0.1015 1.0000
11.250 0.8566 0.03949 0.03095 0.0298 0.0970 1.0000
11.500 0.8677 0.04088 0.03236 0.0302 0.0931 1.0000
11.750 0.8792 0.04225 0.03378 0.0306 0.0895 1.0000
12.000 0.8899 0.04371 0.03524 0.0309 0.0864 1.0000
12.250 0.9010 0.04515 0.03662 0.0313 0.0838 1.0000
12.500 0.9146 0.04646 0.03800 0.0317 0.0812 1.0000
12.750 0.9274 0.04787 0.03949 0.0320 0.0785 1.0000
13.000 0.9400 0.04931 0.04098 0.0322 0.0761 1.0000
13.250 0.9528 0.05075 0.04244 0.0324 0.0742 1.0000
13.500 0.9673 0.05210 0.04377 0.0327 0.0724 1.0000
13.750 0.9819 0.05357 0.04530 0.0330 0.0707 1.0000
14.000 0.9923 0.05540 0.04731 0.0330 0.0690 1.0000
14.250 1.0011 0.05738 0.04943 0.0330 0.0672 1.0000
14.500 1.0099 0.05938 0.05153 0.0329 0.0656 1.0000
14.750 1.0188 0.06141 0.05364 0.0327 0.0641 1.0000
15.000 1.0284 0.06337 0.05564 0.0326 0.0627 1.0000
15.250 1.0429 0.06499 0.05722 0.0326 0.0612 1.0000
15.500 1.0428 0.06808 0.06053 0.0320 0.0601 1.0000
15.750 1.0387 0.07165 0.06435 0.0310 0.0590 1.0000
16.000 1.0338 0.07546 0.06839 0.0298 0.0579 1.0000
16.250 1.0273 0.07958 0.07272 0.0283 0.0568 1.0000
16.500 1.0200 0.08391 0.07724 0.0265 0.0557 1.0000
16.750 1.0126 0.08840 0.08188 0.0245 0.0547 1.0000
17.000 1.0082 0.09249 0.08608 0.0226 0.0536 1.0000
17.250 1.0111 0.09555 0.08916 0.0212 0.0524 1.0000
17.500 1.0095 0.09945 0.09310 0.0195 0.0514 1.0000
17.750 0.9806 0.10806 0.10202 0.0146 0.0510 1.0000
18.000 0.9414 0.11930 0.11357 0.0077 0.0509 1.0000
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