NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 642-015 AIRFOIL (n64015-il) Reynolds number: 500,000 Max Cl/Cd: 65.22 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64015-il-500000.txt Download as CSV file: xf-n64015-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9753 0.09443 0.09136 -0.0163 1.0000 0.0196
-16.250 -1.0243 0.08210 0.07868 -0.0234 1.0000 0.0194
-16.000 -1.0426 0.07582 0.07222 -0.0266 1.0000 0.0194
-15.750 -1.0641 0.06949 0.06567 -0.0293 1.0000 0.0194
-15.500 -1.0786 0.06450 0.06049 -0.0311 1.0000 0.0195
-15.250 -1.0908 0.06008 0.05588 -0.0323 1.0000 0.0195
-15.000 -1.0958 0.05671 0.05238 -0.0331 1.0000 0.0196
-14.750 -1.1000 0.05354 0.04907 -0.0335 1.0000 0.0198
-14.500 -1.1044 0.05036 0.04574 -0.0337 1.0000 0.0199
-14.250 -1.1040 0.04791 0.04318 -0.0337 1.0000 0.0202
-14.000 -1.1050 0.04513 0.04022 -0.0334 1.0000 0.0202
-13.750 -1.1028 0.04284 0.03779 -0.0329 1.0000 0.0205
-13.500 -1.0994 0.04064 0.03544 -0.0323 1.0000 0.0208
-13.250 -1.0938 0.03872 0.03338 -0.0317 1.0000 0.0211
-13.000 -1.0870 0.03691 0.03142 -0.0309 1.0000 0.0214
-12.750 -1.0790 0.03529 0.02965 -0.0301 1.0000 0.0217
-12.500 -1.0698 0.03380 0.02803 -0.0293 1.0000 0.0220
-12.250 -1.0609 0.03259 0.02669 -0.0283 1.0000 0.0222
-12.000 -1.0421 0.03059 0.02463 -0.0277 1.0000 0.0229
-11.750 -1.0272 0.02933 0.02335 -0.0270 1.0000 0.0233
-11.500 -1.0129 0.02822 0.02220 -0.0262 1.0000 0.0237
-11.250 -0.9985 0.02716 0.02110 -0.0254 1.0000 0.0242
-11.000 -0.9839 0.02613 0.02003 -0.0245 1.0000 0.0247
-10.750 -0.9690 0.02513 0.01898 -0.0236 1.0000 0.0253
-10.500 -0.9538 0.02423 0.01801 -0.0227 1.0000 0.0259
-10.250 -0.9383 0.02334 0.01705 -0.0217 1.0000 0.0264
-10.000 -0.9222 0.02259 0.01624 -0.0208 1.0000 0.0269
-9.750 -0.9132 0.02112 0.01478 -0.0191 1.0000 0.0279
-9.500 -0.8996 0.02028 0.01394 -0.0179 1.0000 0.0288
-9.250 -0.8853 0.01951 0.01318 -0.0167 1.0000 0.0296
-8.750 -0.8348 0.01808 0.01162 -0.0181 0.9543 0.0321
-8.500 -0.8257 0.01731 0.01075 -0.0155 0.9260 0.0331
-8.250 -0.8154 0.01668 0.01006 -0.0129 0.9069 0.0346
-8.000 -0.7999 0.01622 0.00953 -0.0110 0.8927 0.0362
-7.750 -0.7820 0.01585 0.00906 -0.0094 0.8806 0.0381
-7.500 -0.7659 0.01521 0.00836 -0.0078 0.8686 0.0405
-7.250 -0.7465 0.01474 0.00786 -0.0066 0.8582 0.0433
-6.750 -0.7056 0.01381 0.00683 -0.0045 0.8388 0.0512
-6.500 -0.6839 0.01338 0.00637 -0.0036 0.8304 0.0577
-6.250 -0.6624 0.01285 0.00589 -0.0028 0.8214 0.0706
-6.000 -0.6421 0.01223 0.00539 -0.0018 0.8134 0.1001
-5.750 -0.6228 0.01141 0.00486 -0.0009 0.8046 0.1569
-5.500 -0.6050 0.01044 0.00427 0.0002 0.7968 0.2428
-5.250 -0.5885 0.00925 0.00364 0.0014 0.7882 0.3635
-5.000 -0.5667 0.00869 0.00340 0.0021 0.7809 0.4551
-4.750 -0.5401 0.00853 0.00329 0.0023 0.7730 0.4871
-4.500 -0.5131 0.00845 0.00317 0.0024 0.7663 0.5071
-4.250 -0.4852 0.00838 0.00309 0.0024 0.7587 0.5231
-4.000 -0.4572 0.00835 0.00300 0.0024 0.7518 0.5357
-3.750 -0.4292 0.00830 0.00293 0.0023 0.7449 0.5463
-3.500 -0.4011 0.00827 0.00288 0.0023 0.7378 0.5583
-3.250 -0.3732 0.00829 0.00284 0.0023 0.7314 0.5716
-3.000 -0.3449 0.00830 0.00283 0.0022 0.7241 0.5834
-2.750 -0.3170 0.00831 0.00283 0.0023 0.7176 0.5952
-2.500 -0.2886 0.00831 0.00281 0.0022 0.7109 0.6046
-2.250 -0.2599 0.00829 0.00277 0.0021 0.7044 0.6103
-2.000 -0.2312 0.00830 0.00269 0.0019 0.6987 0.6152
-1.750 -0.2022 0.00824 0.00264 0.0016 0.6923 0.6201
-1.500 -0.1735 0.00822 0.00260 0.0015 0.6864 0.6252
-1.250 -0.1447 0.00823 0.00256 0.0012 0.6810 0.6304
-1.000 -0.1156 0.00820 0.00251 0.0009 0.6750 0.6350
-0.750 -0.0868 0.00816 0.00248 0.0008 0.6696 0.6393
-0.500 -0.0580 0.00818 0.00247 0.0005 0.6644 0.6441
-0.250 -0.0288 0.00817 0.00245 0.0002 0.6586 0.6491
0.000 0.0000 0.00814 0.00243 0.0000 0.6536 0.6536
0.250 0.0288 0.00817 0.00245 -0.0002 0.6490 0.6586
0.500 0.0580 0.00818 0.00247 -0.0005 0.6440 0.6644
0.750 0.0869 0.00816 0.00248 -0.0008 0.6393 0.6696
1.000 0.1156 0.00820 0.00251 -0.0009 0.6350 0.6750
1.250 0.1447 0.00823 0.00256 -0.0012 0.6304 0.6810
1.500 0.1736 0.00822 0.00260 -0.0015 0.6252 0.6864
1.750 0.2023 0.00824 0.00264 -0.0016 0.6201 0.6923
2.000 0.2312 0.00830 0.00269 -0.0019 0.6152 0.6987
2.250 0.2600 0.00829 0.00277 -0.0021 0.6103 0.7044
2.500 0.2886 0.00831 0.00281 -0.0022 0.6045 0.7109
2.750 0.3171 0.00831 0.00283 -0.0023 0.5952 0.7176
3.000 0.3449 0.00830 0.00283 -0.0022 0.5834 0.7241
3.250 0.3733 0.00829 0.00284 -0.0023 0.5716 0.7314
3.500 0.4012 0.00827 0.00288 -0.0023 0.5582 0.7378
3.750 0.4293 0.00830 0.00293 -0.0023 0.5463 0.7449
4.000 0.4572 0.00835 0.00300 -0.0024 0.5357 0.7518
4.250 0.4852 0.00838 0.00309 -0.0024 0.5231 0.7587
4.500 0.5131 0.00845 0.00317 -0.0024 0.5072 0.7663
4.750 0.5401 0.00853 0.00329 -0.0023 0.4870 0.7730
5.000 0.5668 0.00869 0.00340 -0.0021 0.4548 0.7809
5.250 0.5884 0.00925 0.00364 -0.0014 0.3627 0.7882
5.500 0.6051 0.01043 0.00427 -0.0002 0.2437 0.7968
5.750 0.6229 0.01141 0.00486 0.0009 0.1574 0.8046
6.000 0.6421 0.01223 0.00539 0.0018 0.1002 0.8134
6.250 0.6625 0.01285 0.00589 0.0028 0.0707 0.8214
6.500 0.6840 0.01338 0.00637 0.0036 0.0578 0.8304
6.750 0.7056 0.01381 0.00683 0.0045 0.0512 0.8388
7.250 0.7466 0.01474 0.00786 0.0066 0.0433 0.8582
7.500 0.7659 0.01521 0.00836 0.0077 0.0405 0.8686
7.750 0.7821 0.01584 0.00905 0.0094 0.0380 0.8806
8.000 0.8001 0.01622 0.00952 0.0109 0.0361 0.8927
8.250 0.8155 0.01668 0.01006 0.0128 0.0346 0.9070
8.500 0.8259 0.01732 0.01075 0.0155 0.0331 0.9260
8.750 0.8350 0.01808 0.01162 0.0181 0.0321 0.9543
9.250 0.8855 0.01952 0.01319 0.0167 0.0297 1.0000
9.500 0.9003 0.02024 0.01390 0.0178 0.0287 1.0000
9.750 0.9133 0.02113 0.01479 0.0191 0.0279 1.0000
10.000 0.9226 0.02257 0.01622 0.0207 0.0268 1.0000
10.250 0.9388 0.02331 0.01703 0.0216 0.0264 1.0000
10.500 0.9542 0.02419 0.01798 0.0226 0.0258 1.0000
10.750 0.9694 0.02514 0.01898 0.0235 0.0253 1.0000
11.000 0.9843 0.02613 0.02003 0.0244 0.0246 1.0000
11.250 0.9987 0.02712 0.02105 0.0253 0.0240 1.0000
11.500 1.0133 0.02821 0.02218 0.0261 0.0237 1.0000
11.750 1.0275 0.02930 0.02331 0.0269 0.0232 1.0000
12.000 1.0426 0.03059 0.02463 0.0277 0.0229 1.0000
12.250 1.0637 0.03268 0.02677 0.0282 0.0223 1.0000
12.500 1.0705 0.03384 0.02807 0.0292 0.0220 1.0000
12.750 1.0787 0.03524 0.02961 0.0301 0.0216 1.0000
13.000 1.0871 0.03684 0.03135 0.0309 0.0213 1.0000
13.250 1.0943 0.03869 0.03335 0.0316 0.0210 1.0000
13.500 1.0997 0.04068 0.03549 0.0323 0.0207 1.0000
13.750 1.1037 0.04275 0.03769 0.0328 0.0204 1.0000
14.000 1.1057 0.04512 0.04020 0.0333 0.0202 1.0000
14.250 1.1069 0.04752 0.04274 0.0335 0.0200 1.0000
14.500 1.1035 0.05059 0.04598 0.0336 0.0199 1.0000
14.750 1.0993 0.05374 0.04930 0.0334 0.0198 1.0000
15.000 1.0945 0.05697 0.05267 0.0329 0.0197 1.0000
15.250 1.0926 0.05991 0.05570 0.0323 0.0195 1.0000
15.500 1.0838 0.06385 0.05979 0.0312 0.0193 1.0000
15.750 1.0659 0.06933 0.06550 0.0293 0.0194 1.0000
16.000 1.0472 0.07523 0.07160 0.0268 0.0194 1.0000
16.250 1.0306 0.08117 0.07770 0.0238 0.0193 1.0000
16.500 0.9609 0.09736 0.09439 0.0144 0.0197 1.0000
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