NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 642-015A AIRFOIL (n64015a-il) Reynolds number: 500,000 Max Cl/Cd: 64.38 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64015a-il-500000.txt Download as CSV file: xf-n64015a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015A 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9958 0.09366 0.09041 -0.0242 1.0000 0.0187
-16.500 -1.0245 0.08506 0.08157 -0.0290 1.0000 0.0186
-16.250 -1.0456 0.07837 0.07469 -0.0323 1.0000 0.0186
-16.000 -1.0642 0.07248 0.06861 -0.0347 1.0000 0.0186
-15.750 -1.0800 0.06734 0.06331 -0.0364 1.0000 0.0187
-15.500 -1.0929 0.06281 0.05860 -0.0375 1.0000 0.0187
-15.250 -1.1033 0.05876 0.05439 -0.0382 1.0000 0.0188
-15.000 -1.1104 0.05521 0.05070 -0.0385 1.0000 0.0189
-14.750 -1.1151 0.05204 0.04737 -0.0386 1.0000 0.0190
-14.500 -1.1176 0.04919 0.04439 -0.0384 1.0000 0.0192
-14.250 -1.1181 0.04660 0.04167 -0.0381 1.0000 0.0193
-14.000 -1.1170 0.04423 0.03917 -0.0376 1.0000 0.0195
-13.750 -1.1143 0.04202 0.03683 -0.0369 1.0000 0.0197
-13.500 -1.1094 0.04003 0.03472 -0.0362 1.0000 0.0199
-13.250 -1.1032 0.03816 0.03274 -0.0353 1.0000 0.0201
-13.000 -1.0957 0.03640 0.03085 -0.0344 1.0000 0.0204
-12.750 -1.0868 0.03474 0.02906 -0.0334 1.0000 0.0207
-12.500 -1.0766 0.03321 0.02740 -0.0324 1.0000 0.0210
-12.250 -1.0655 0.03184 0.02590 -0.0314 1.0000 0.0214
-12.000 -1.0536 0.03060 0.02454 -0.0303 1.0000 0.0218
-11.750 -1.0410 0.02951 0.02332 -0.0292 1.0000 0.0221
-11.500 -1.0259 0.02798 0.02170 -0.0282 1.0000 0.0225
-11.250 -1.0112 0.02649 0.02017 -0.0271 1.0000 0.0230
-11.000 -0.9971 0.02538 0.01904 -0.0260 1.0000 0.0234
-10.750 -0.9826 0.02441 0.01804 -0.0248 1.0000 0.0239
-10.500 -0.9680 0.02349 0.01708 -0.0236 1.0000 0.0244
-10.250 -0.9533 0.02261 0.01615 -0.0223 1.0000 0.0250
-10.000 -0.9387 0.02178 0.01526 -0.0209 1.0000 0.0256
-9.750 -0.9242 0.02101 0.01444 -0.0194 1.0000 0.0262
-9.500 -0.9090 0.02040 0.01376 -0.0178 1.0000 0.0268
-9.250 -0.9031 0.01931 0.01265 -0.0147 1.0000 0.0276
-9.000 -0.8946 0.01863 0.01198 -0.0118 1.0000 0.0285
-8.750 -0.8837 0.01810 0.01144 -0.0092 1.0000 0.0295
-8.500 -0.8755 0.01764 0.01096 -0.0060 1.0000 0.0304
-8.000 -0.8336 0.01629 0.00955 -0.0049 0.9943 0.0334
-7.750 -0.8003 0.01558 0.00883 -0.0069 0.9881 0.0361
-7.500 -0.7650 0.01495 0.00817 -0.0091 0.9828 0.0394
-7.250 -0.7342 0.01430 0.00754 -0.0104 0.9728 0.0443
-7.000 -0.7046 0.01368 0.00694 -0.0113 0.9613 0.0509
-6.750 -0.6773 0.01314 0.00641 -0.0116 0.9479 0.0596
-6.500 -0.6536 0.01263 0.00594 -0.0111 0.9326 0.0722
-6.250 -0.6321 0.01214 0.00550 -0.0101 0.9170 0.0917
-6.000 -0.6128 0.01154 0.00505 -0.0088 0.9017 0.1273
-5.750 -0.5947 0.01082 0.00457 -0.0074 0.8874 0.1856
-5.500 -0.5782 0.00996 0.00405 -0.0057 0.8742 0.2691
-5.250 -0.5636 0.00896 0.00354 -0.0038 0.8613 0.3791
-5.000 -0.5440 0.00845 0.00333 -0.0024 0.8502 0.4628
-4.750 -0.5196 0.00830 0.00320 -0.0018 0.8404 0.4996
-4.500 -0.4942 0.00818 0.00310 -0.0013 0.8300 0.5232
-4.250 -0.4680 0.00812 0.00301 -0.0010 0.8210 0.5410
-4.000 -0.4415 0.00807 0.00293 -0.0007 0.8120 0.5557
-3.750 -0.4147 0.00804 0.00286 -0.0005 0.8037 0.5695
-3.500 -0.3877 0.00802 0.00279 -0.0003 0.7951 0.5818
-3.250 -0.3606 0.00799 0.00273 -0.0001 0.7870 0.5920
-3.000 -0.3338 0.00797 0.00269 0.0001 0.7787 0.6045
-2.750 -0.3069 0.00798 0.00268 0.0003 0.7711 0.6182
-2.500 -0.2797 0.00800 0.00265 0.0005 0.7633 0.6291
-2.250 -0.2522 0.00799 0.00263 0.0006 0.7564 0.6380
-2.000 -0.2246 0.00797 0.00259 0.0006 0.7487 0.6464
-1.500 -0.1687 0.00795 0.00251 0.0005 0.7343 0.6594
-1.250 -0.1407 0.00792 0.00246 0.0005 0.7274 0.6646
-1.000 -0.1125 0.00790 0.00244 0.0004 0.7206 0.6704
-0.500 -0.0563 0.00789 0.00238 0.0002 0.7078 0.6822
-0.250 -0.0281 0.00787 0.00238 0.0001 0.7008 0.6883
0.000 0.0000 0.00788 0.00235 0.0000 0.6946 0.6946
0.250 0.0281 0.00787 0.00238 -0.0001 0.6884 0.7008
0.500 0.0563 0.00789 0.00238 -0.0002 0.6822 0.7078
1.000 0.1125 0.00790 0.00244 -0.0004 0.6704 0.7206
1.250 0.1407 0.00792 0.00246 -0.0005 0.6646 0.7274
1.500 0.1687 0.00795 0.00251 -0.0005 0.6593 0.7343
2.000 0.2246 0.00797 0.00259 -0.0006 0.6464 0.7487
2.250 0.2522 0.00799 0.00263 -0.0006 0.6380 0.7564
2.500 0.2797 0.00800 0.00265 -0.0005 0.6290 0.7633
2.750 0.3069 0.00798 0.00268 -0.0003 0.6182 0.7711
3.000 0.3338 0.00797 0.00269 -0.0001 0.6046 0.7787
3.250 0.3606 0.00799 0.00273 0.0001 0.5920 0.7870
3.500 0.3877 0.00802 0.00279 0.0003 0.5818 0.7952
3.750 0.4148 0.00804 0.00286 0.0005 0.5695 0.8037
4.000 0.4415 0.00807 0.00293 0.0007 0.5557 0.8120
4.250 0.4681 0.00812 0.00301 0.0010 0.5410 0.8210
4.500 0.4943 0.00818 0.00310 0.0013 0.5232 0.8300
4.750 0.5196 0.00830 0.00320 0.0018 0.4997 0.8404
5.000 0.5440 0.00845 0.00333 0.0024 0.4628 0.8502
5.250 0.5637 0.00896 0.00354 0.0038 0.3796 0.8613
5.500 0.5782 0.00996 0.00405 0.0057 0.2691 0.8742
5.750 0.5948 0.01082 0.00457 0.0073 0.1856 0.8874
6.000 0.6128 0.01154 0.00505 0.0088 0.1273 0.9017
6.250 0.6322 0.01214 0.00550 0.0101 0.0916 0.9169
6.500 0.6537 0.01263 0.00594 0.0111 0.0722 0.9326
6.750 0.6774 0.01314 0.00641 0.0116 0.0596 0.9479
7.000 0.7048 0.01368 0.00694 0.0113 0.0508 0.9613
7.250 0.7343 0.01430 0.00754 0.0104 0.0444 0.9728
7.500 0.7650 0.01495 0.00817 0.0091 0.0394 0.9829
7.750 0.8004 0.01558 0.00883 0.0069 0.0361 0.9882
8.000 0.8337 0.01629 0.00955 0.0049 0.0334 0.9943
8.250 0.8669 0.01722 0.01051 0.0028 0.0314 0.9994
8.500 0.8754 0.01764 0.01096 0.0060 0.0304 1.0000
8.750 0.8838 0.01810 0.01143 0.0092 0.0295 1.0000
9.000 0.8948 0.01863 0.01197 0.0118 0.0285 1.0000
9.250 0.9033 0.01931 0.01265 0.0147 0.0276 1.0000
9.500 0.9094 0.02039 0.01375 0.0177 0.0268 1.0000
9.750 0.9246 0.02101 0.01444 0.0193 0.0262 1.0000
10.000 0.9392 0.02178 0.01526 0.0208 0.0256 1.0000
10.250 0.9538 0.02261 0.01615 0.0222 0.0250 1.0000
10.500 0.9685 0.02349 0.01708 0.0235 0.0244 1.0000
10.750 0.9832 0.02440 0.01803 0.0247 0.0239 1.0000
11.000 0.9977 0.02538 0.01904 0.0258 0.0234 1.0000
11.250 1.0119 0.02648 0.02017 0.0270 0.0230 1.0000
11.500 1.0266 0.02798 0.02170 0.0281 0.0225 1.0000
11.750 1.0418 0.02951 0.02332 0.0291 0.0221 1.0000
12.000 1.0544 0.03060 0.02454 0.0302 0.0218 1.0000
12.250 1.0664 0.03183 0.02590 0.0312 0.0214 1.0000
12.500 1.0776 0.03321 0.02740 0.0322 0.0210 1.0000
12.750 1.0878 0.03474 0.02906 0.0332 0.0207 1.0000
13.000 1.0967 0.03640 0.03085 0.0342 0.0204 1.0000
13.250 1.1043 0.03816 0.03274 0.0351 0.0201 1.0000
13.500 1.1106 0.04004 0.03473 0.0360 0.0199 1.0000
13.750 1.1155 0.04202 0.03683 0.0367 0.0197 1.0000
14.000 1.1183 0.04422 0.03916 0.0374 0.0195 1.0000
14.250 1.1194 0.04660 0.04167 0.0379 0.0193 1.0000
14.500 1.1190 0.04918 0.04439 0.0382 0.0191 1.0000
14.750 1.1166 0.05203 0.04736 0.0383 0.0190 1.0000
15.000 1.1119 0.05522 0.05070 0.0383 0.0189 1.0000
15.250 1.1046 0.05880 0.05444 0.0379 0.0188 1.0000
15.500 1.0944 0.06283 0.05863 0.0372 0.0187 1.0000
15.750 1.0815 0.06738 0.06334 0.0361 0.0187 1.0000
16.000 1.0656 0.07253 0.06867 0.0344 0.0186 1.0000
16.250 1.0471 0.07840 0.07472 0.0319 0.0186 1.0000
16.500 1.0257 0.08516 0.08168 0.0287 0.0186 1.0000
16.750 0.9988 0.09346 0.09020 0.0240 0.0187 1.0000
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