GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 373 AIRFOIL (goe373-il) Reynolds number: 500,000 Max Cl/Cd: 94.79 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe373-il-500000-n5.txt Download as CSV file: xf-goe373-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 373 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2892 0.09413 0.09197 -0.0224 1.0000 0.0123
-7.750 -0.2879 0.09173 0.08961 -0.0218 1.0000 0.0110
-7.500 -0.2878 0.08899 0.08690 -0.0219 0.9996 0.0105
-7.250 -0.2729 0.08511 0.08303 -0.0262 0.9910 0.0103
-7.000 -0.2556 0.08088 0.07881 -0.0314 0.9801 0.0101
-6.750 -0.2335 0.07712 0.07504 -0.0370 0.9701 0.0105
-6.500 -0.2061 0.07305 0.07094 -0.0440 0.9603 0.0111
-6.250 -0.1729 0.06829 0.06614 -0.0527 0.9487 0.0118
-6.000 -0.1360 0.06340 0.06118 -0.0620 0.9314 0.0119
-5.750 -0.0982 0.05847 0.05613 -0.0711 0.9037 0.0119
-5.500 -0.0703 0.05410 0.05157 -0.0772 0.8694 0.0121
-5.250 -0.0460 0.04962 0.04688 -0.0821 0.8402 0.0126
-5.000 -0.0253 0.04768 0.04478 -0.0835 0.8170 0.0129
-4.750 -0.0026 0.04532 0.04228 -0.0855 0.7977 0.0132
-4.500 0.0215 0.04285 0.03967 -0.0876 0.7808 0.0138
-4.250 0.0474 0.04016 0.03680 -0.0897 0.7644 0.0149
-4.000 0.0827 0.03444 0.03074 -0.0939 0.7511 0.0159
-3.750 0.1051 0.03309 0.02928 -0.0944 0.7354 0.0163
-3.500 0.1299 0.03153 0.02759 -0.0950 0.7216 0.0169
-3.250 0.1646 0.02788 0.02356 -0.0964 0.7105 0.0200
-3.000 0.1861 0.02713 0.02277 -0.0966 0.6975 0.0206
-2.750 0.2196 0.02595 0.02120 -0.0965 0.6850 0.0240
-2.500 0.2471 0.02420 0.01913 -0.0965 0.6711 0.0241
-2.250 0.2714 0.02148 0.01620 -0.0968 0.6558 0.0245
-2.000 0.2958 0.02008 0.01467 -0.0969 0.6374 0.0248
-1.750 0.3208 0.01901 0.01344 -0.0968 0.6174 0.0253
-1.500 0.3465 0.01806 0.01227 -0.0966 0.5981 0.0260
-1.250 0.3728 0.01718 0.01117 -0.0963 0.5805 0.0270
-1.000 0.4003 0.01676 0.01048 -0.0957 0.5651 0.0291
-0.750 0.4277 0.01663 0.01006 -0.0952 0.5516 0.0296
-0.500 0.4543 0.01618 0.00938 -0.0948 0.5396 0.0297
-0.250 0.4808 0.01558 0.00861 -0.0945 0.5282 0.0298
0.000 0.5074 0.01502 0.00789 -0.0942 0.5174 0.0298
0.250 0.5337 0.01380 0.00649 -0.0940 0.5061 0.0302
0.500 0.5598 0.01299 0.00558 -0.0937 0.4944 0.0308
1.000 0.6127 0.01210 0.00456 -0.0931 0.4710 0.0316
1.250 0.6396 0.01192 0.00429 -0.0927 0.4601 0.0285
1.500 0.6659 0.01150 0.00379 -0.0923 0.4480 0.0271
1.750 0.6923 0.01125 0.00347 -0.0919 0.4353 0.0265
2.000 0.7185 0.01107 0.00323 -0.0915 0.4221 0.0266
2.250 0.7445 0.01096 0.00306 -0.0911 0.4069 0.0270
2.500 0.7704 0.01091 0.00295 -0.0907 0.3920 0.0276
2.750 0.7962 0.01089 0.00288 -0.0903 0.3791 0.0281
3.000 0.8222 0.01095 0.00290 -0.0899 0.3665 0.0290
3.250 0.8480 0.01090 0.00283 -0.0896 0.3557 0.0309
3.500 0.8739 0.01095 0.00287 -0.0892 0.3464 0.0307
3.750 0.8995 0.01108 0.00296 -0.0888 0.3338 0.0303
4.500 0.9766 0.01138 0.00324 -0.0877 0.3047 0.0297
4.750 1.0025 0.01147 0.00334 -0.0873 0.2969 0.0297
5.000 1.0281 0.01160 0.00346 -0.0870 0.2882 0.0299
5.250 1.0535 0.01177 0.00358 -0.0865 0.2761 0.0305
5.500 1.0782 0.01201 0.00374 -0.0861 0.2546 0.0318
5.750 1.1016 0.01241 0.00399 -0.0854 0.2203 0.0338
6.000 1.1243 0.01289 0.00430 -0.0847 0.1879 0.0381
6.250 1.1476 0.01330 0.00464 -0.0840 0.1707 0.0439
6.500 1.1744 0.01239 0.00522 -0.0846 0.1582 1.0000
6.750 1.1980 0.01277 0.00557 -0.0839 0.1482 1.0000
7.000 1.2204 0.01327 0.00599 -0.0832 0.1291 1.0000
7.250 1.2392 0.01414 0.00656 -0.0820 0.0858 1.0000
7.500 1.2570 0.01511 0.00729 -0.0806 0.0531 1.0000
7.750 1.2733 0.01620 0.00818 -0.0791 0.0184 1.0000
8.000 1.2939 0.01682 0.00884 -0.0780 0.0127 1.0000
8.250 1.3146 0.01740 0.00950 -0.0769 0.0102 1.0000
8.500 1.3354 0.01793 0.01012 -0.0759 0.0086 1.0000
8.750 1.3549 0.01856 0.01082 -0.0747 0.0073 1.0000
9.000 1.3718 0.01941 0.01179 -0.0731 0.0062 1.0000
9.250 1.3901 0.02008 0.01253 -0.0717 0.0058 1.0000
9.500 1.4080 0.02073 0.01329 -0.0703 0.0053 1.0000
9.750 1.4242 0.02148 0.01412 -0.0688 0.0050 1.0000
10.000 1.4386 0.02231 0.01505 -0.0669 0.0047 1.0000
10.250 1.4509 0.02316 0.01598 -0.0648 0.0044 1.0000
10.500 1.4591 0.02411 0.01702 -0.0620 0.0042 1.0000
10.750 1.4659 0.02513 0.01814 -0.0592 0.0041 1.0000
11.000 1.4716 0.02626 0.01936 -0.0565 0.0039 1.0000
11.250 1.4749 0.02760 0.02082 -0.0537 0.0038 1.0000
11.500 1.4758 0.02920 0.02254 -0.0511 0.0037 1.0000
11.750 1.4736 0.03119 0.02465 -0.0487 0.0036 1.0000
12.000 1.4708 0.03344 0.02702 -0.0468 0.0035 1.0000
12.250 1.4638 0.03632 0.03005 -0.0452 0.0034 1.0000
12.500 1.4470 0.04054 0.03443 -0.0440 0.0033 1.0000
12.750 1.4417 0.04384 0.03787 -0.0436 0.0033 1.0000
13.000 1.4379 0.04717 0.04131 -0.0436 0.0032 1.0000
13.250 1.4340 0.05068 0.04495 -0.0438 0.0032 1.0000
13.500 1.4290 0.05450 0.04890 -0.0444 0.0032 1.0000
13.750 1.4231 0.05859 0.05312 -0.0452 0.0032 1.0000
14.000 1.4166 0.06291 0.05756 -0.0462 0.0031 1.0000
14.250 1.4091 0.06745 0.06222 -0.0473 0.0032 1.0000
14.500 1.4023 0.07205 0.06696 -0.0486 0.0031 1.0000
14.750 1.3957 0.07675 0.07178 -0.0501 0.0031 1.0000
15.000 1.3888 0.08159 0.07674 -0.0517 0.0031 1.0000
15.250 1.3821 0.08657 0.08185 -0.0534 0.0030 1.0000
15.500 1.3754 0.09163 0.08703 -0.0553 0.0031 1.0000
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Polar data table (+)
Polar graphs
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