HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il) Reynolds number: 50,000 Max Cl/Cd: 32.34 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1512-il-50000.txt Download as CSV file: xf-hq1512-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4272 0.10332 0.09627 -0.0111 1.0000 0.3333
-9.000 -0.4406 0.10156 0.09466 -0.0113 1.0000 0.3456
-8.500 -0.5992 0.06904 0.06237 -0.0453 1.0000 0.1379
-8.250 -0.6017 0.06461 0.05792 -0.0448 1.0000 0.1353
-8.000 -0.6135 0.05997 0.05313 -0.0441 1.0000 0.1316
-7.750 -0.6421 0.05479 0.04722 -0.0425 1.0000 0.1246
-7.500 -0.6398 0.05104 0.04324 -0.0407 1.0000 0.1240
-7.250 -0.6369 0.04750 0.03937 -0.0386 1.0000 0.1236
-7.000 -0.6327 0.04421 0.03565 -0.0363 1.0000 0.1239
-6.750 -0.6239 0.04132 0.03257 -0.0343 1.0000 0.1273
-6.500 -0.6120 0.03915 0.03025 -0.0323 1.0000 0.1334
-6.250 -0.6004 0.03656 0.02711 -0.0302 1.0000 0.1377
-6.000 -0.5849 0.03424 0.02468 -0.0285 1.0000 0.1447
-5.750 -0.5693 0.03230 0.02241 -0.0267 1.0000 0.1556
-5.500 -0.5515 0.03049 0.02042 -0.0251 1.0000 0.1689
-5.250 -0.5338 0.02889 0.01894 -0.0235 1.0000 0.1880
-5.000 -0.5154 0.02736 0.01737 -0.0218 1.0000 0.2134
-4.750 -0.4974 0.02579 0.01602 -0.0201 1.0000 0.2476
-4.500 -0.4805 0.02416 0.01471 -0.0182 1.0000 0.3017
-4.250 -0.4661 0.02250 0.01389 -0.0159 1.0000 0.3916
-4.000 -0.4589 0.02188 0.01431 -0.0107 1.0000 0.5270
-3.750 -0.4546 0.02255 0.01533 -0.0038 1.0000 0.6308
-3.500 -0.4503 0.02330 0.01614 0.0032 1.0000 0.6952
-3.250 -0.4461 0.02379 0.01655 0.0099 1.0000 0.7469
-3.000 -0.4413 0.02407 0.01677 0.0164 1.0000 0.7906
-2.750 -0.4337 0.02418 0.01679 0.0222 1.0000 0.8323
-2.500 -0.4146 0.02434 0.01680 0.0259 1.0000 0.8755
-2.250 -0.3322 0.02543 0.01743 0.0189 1.0000 0.9270
-2.000 -0.1768 0.02633 0.01761 -0.0036 1.0000 0.9695
-1.750 -0.0661 0.02605 0.01689 -0.0206 1.0000 1.0000
-1.500 -0.0741 0.02582 0.01663 -0.0174 1.0000 1.0000
-1.250 -0.0824 0.02555 0.01632 -0.0142 1.0000 1.0000
-1.000 -0.0913 0.02523 0.01597 -0.0108 1.0000 1.0000
-0.750 -0.1010 0.02485 0.01555 -0.0073 1.0000 1.0000
-0.500 -0.1112 0.02440 0.01507 -0.0036 1.0000 1.0000
-0.250 -0.1195 0.02395 0.01456 -0.0002 1.0000 1.0000
0.000 -0.1198 0.02370 0.01421 0.0020 1.0000 1.0000
0.250 -0.1098 0.02376 0.01414 0.0028 1.0000 1.0000
0.500 -0.0948 0.02402 0.01426 0.0028 1.0000 1.0000
0.750 -0.0775 0.02441 0.01452 0.0026 1.0000 1.0000
1.000 -0.0461 0.02526 0.01526 -0.0002 0.9947 1.0000
1.250 0.0008 0.02658 0.01646 -0.0057 0.9825 1.0000
1.500 0.0444 0.02778 0.01758 -0.0105 0.9695 1.0000
1.750 0.0863 0.02891 0.01865 -0.0148 0.9556 1.0000
2.000 0.1307 0.03005 0.01976 -0.0193 0.9393 1.0000
2.250 0.1729 0.03095 0.02066 -0.0230 0.9182 1.0000
2.500 0.2301 0.03198 0.02172 -0.0287 0.8962 1.0000
2.750 0.2653 0.03267 0.02244 -0.0307 0.8751 1.0000
3.000 0.3080 0.03341 0.02323 -0.0337 0.8553 1.0000
3.250 0.3583 0.03403 0.02396 -0.0374 0.8360 1.0000
3.500 0.3869 0.03460 0.02460 -0.0379 0.8142 1.0000
3.750 0.4369 0.03486 0.02503 -0.0409 0.7935 1.0000
4.000 0.4713 0.03519 0.02547 -0.0415 0.7707 1.0000
4.250 0.5274 0.03481 0.02533 -0.0444 0.7490 1.0000
4.500 0.5640 0.03470 0.02537 -0.0445 0.7244 1.0000
4.750 0.6221 0.03341 0.02432 -0.0459 0.7033 1.0000
5.000 0.6555 0.03287 0.02396 -0.0447 0.6767 1.0000
5.250 0.6932 0.03199 0.02324 -0.0435 0.6502 1.0000
5.500 0.7335 0.03080 0.02219 -0.0423 0.6232 1.0000
5.750 0.7706 0.02971 0.02121 -0.0407 0.5944 1.0000
6.000 0.8036 0.02885 0.02040 -0.0389 0.5636 1.0000
6.250 0.8345 0.02815 0.01968 -0.0370 0.5311 1.0000
6.500 0.8651 0.02755 0.01896 -0.0351 0.4970 1.0000
6.750 0.8860 0.02773 0.01907 -0.0328 0.4608 1.0000
7.250 0.9269 0.02866 0.01963 -0.0284 0.3837 1.0000
7.500 0.9440 0.02964 0.02042 -0.0262 0.3429 1.0000
7.750 0.9613 0.03101 0.02149 -0.0241 0.3019 1.0000
8.000 0.9790 0.03286 0.02311 -0.0224 0.2647 1.0000
8.250 0.9971 0.03486 0.02500 -0.0208 0.2352 1.0000
8.500 1.0150 0.03688 0.02701 -0.0195 0.2132 1.0000
8.750 1.0341 0.03922 0.02950 -0.0183 0.1978 1.0000
9.000 1.0526 0.04149 0.03191 -0.0171 0.1850 1.0000
9.250 1.0729 0.04358 0.03398 -0.0163 0.1735 1.0000
9.500 1.0793 0.04662 0.03758 -0.0141 0.1670 1.0000
9.750 1.1031 0.04935 0.04023 -0.0138 0.1600 1.0000
10.000 1.0977 0.05298 0.04450 -0.0109 0.1569 1.0000
10.250 1.0929 0.05652 0.04846 -0.0085 0.1531 1.0000
10.500 1.1192 0.05905 0.05083 -0.0085 0.1461 1.0000
10.750 1.1057 0.06333 0.05556 -0.0059 0.1455 1.0000
11.000 1.0882 0.06781 0.06037 -0.0036 0.1453 1.0000
11.250 1.0657 0.07232 0.06512 -0.0014 0.1456 1.0000
11.500 1.0427 0.07709 0.07003 0.0001 0.1461 1.0000
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Polar data table (+)
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