HQ 1.5/12 AIRFOIL (hq1512-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/12 AIRFOIL (hq1512-il) Reynolds number: 200,000 Max Cl/Cd: 60.33 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1512-il-200000-n5.txt Download as CSV file: xf-hq1512-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7468 0.05858 0.05432 -0.0547 1.0000 0.0134
-12.000 -0.7643 0.05323 0.04879 -0.0579 1.0000 0.0134
-11.750 -0.7872 0.04783 0.04312 -0.0601 1.0000 0.0133
-11.500 -0.7930 0.04513 0.04031 -0.0606 1.0000 0.0135
-11.250 -0.8011 0.04244 0.03748 -0.0602 1.0000 0.0137
-11.000 -0.8084 0.04021 0.03510 -0.0588 1.0000 0.0139
-10.750 -0.8144 0.03828 0.03301 -0.0564 1.0000 0.0141
-10.500 -0.8152 0.03611 0.03061 -0.0544 1.0000 0.0143
-10.250 -0.8112 0.03427 0.02857 -0.0525 1.0000 0.0148
-10.000 -0.8053 0.03234 0.02641 -0.0505 1.0000 0.0152
-9.750 -0.7973 0.03055 0.02438 -0.0486 1.0000 0.0156
-9.500 -0.7874 0.02897 0.02256 -0.0465 1.0000 0.0162
-9.250 -0.7758 0.02768 0.02104 -0.0445 1.0000 0.0170
-9.000 -0.7654 0.02628 0.01951 -0.0424 1.0000 0.0178
-8.750 -0.7544 0.02536 0.01856 -0.0403 1.0000 0.0185
-8.500 -0.7307 0.02426 0.01737 -0.0405 0.9960 0.0194
-8.250 -0.7006 0.02298 0.01594 -0.0419 0.9891 0.0205
-8.000 -0.6689 0.02175 0.01454 -0.0435 0.9834 0.0218
-7.750 -0.6389 0.02071 0.01333 -0.0446 0.9763 0.0233
-7.500 -0.6073 0.01967 0.01226 -0.0462 0.9706 0.0254
-7.250 -0.5783 0.01883 0.01135 -0.0470 0.9620 0.0273
-7.000 -0.5460 0.01798 0.01037 -0.0484 0.9560 0.0296
-6.750 -0.5185 0.01713 0.00948 -0.0489 0.9465 0.0327
-6.500 -0.4878 0.01651 0.00878 -0.0499 0.9391 0.0372
-6.250 -0.4593 0.01582 0.00805 -0.0504 0.9304 0.0427
-6.000 -0.4304 0.01529 0.00744 -0.0509 0.9223 0.0500
-5.750 -0.4019 0.01474 0.00690 -0.0513 0.9145 0.0612
-5.500 -0.3750 0.01426 0.00642 -0.0514 0.9059 0.0750
-5.250 -0.3475 0.01378 0.00598 -0.0515 0.8986 0.0942
-5.000 -0.3225 0.01333 0.00562 -0.0512 0.8895 0.1200
-4.750 -0.2967 0.01287 0.00526 -0.0511 0.8820 0.1527
-4.250 -0.2466 0.01206 0.00465 -0.0504 0.8661 0.2312
-4.000 -0.2221 0.01163 0.00436 -0.0500 0.8582 0.2787
-3.750 -0.1986 0.01110 0.00411 -0.0494 0.8510 0.3514
-3.500 -0.1752 0.01066 0.00397 -0.0487 0.8432 0.4361
-3.250 -0.1504 0.01042 0.00391 -0.0480 0.8364 0.5005
-3.000 -0.1249 0.01031 0.00388 -0.0474 0.8289 0.5451
-2.750 -0.0983 0.01026 0.00383 -0.0469 0.8225 0.5753
-2.500 -0.0717 0.01023 0.00379 -0.0465 0.8149 0.5986
-2.250 -0.0446 0.01022 0.00374 -0.0461 0.8087 0.6187
-2.000 -0.0180 0.01021 0.00373 -0.0457 0.8010 0.6371
-1.750 0.0092 0.01021 0.00367 -0.0453 0.7949 0.6528
-1.500 0.0361 0.01021 0.00366 -0.0450 0.7870 0.6661
-1.250 0.0634 0.01021 0.00362 -0.0446 0.7807 0.6794
-1.000 0.0901 0.01022 0.00363 -0.0442 0.7728 0.6933
-0.750 0.1173 0.01023 0.00360 -0.0439 0.7663 0.7064
-0.500 0.1439 0.01023 0.00362 -0.0434 0.7577 0.7173
-0.250 0.1708 0.01023 0.00358 -0.0430 0.7490 0.7273
0.000 0.1978 0.01022 0.00354 -0.0427 0.7385 0.7366
0.250 0.2246 0.01021 0.00353 -0.0423 0.7283 0.7435
0.500 0.2520 0.01022 0.00348 -0.0420 0.7189 0.7515
0.750 0.2787 0.01021 0.00348 -0.0416 0.7085 0.7584
1.000 0.3057 0.01022 0.00347 -0.0413 0.6974 0.7666
1.250 0.3323 0.01022 0.00348 -0.0409 0.6861 0.7740
1.500 0.3592 0.01024 0.00348 -0.0406 0.6755 0.7823
1.750 0.3858 0.01025 0.00351 -0.0402 0.6649 0.7902
2.000 0.4125 0.01027 0.00357 -0.0398 0.6541 0.7986
2.250 0.4390 0.01030 0.00361 -0.0394 0.6425 0.8075
2.500 0.4652 0.01033 0.00366 -0.0390 0.6299 0.8163
2.750 0.4915 0.01037 0.00372 -0.0385 0.6165 0.8260
3.000 0.5173 0.01040 0.00379 -0.0380 0.6011 0.8361
3.250 0.5430 0.01045 0.00386 -0.0374 0.5836 0.8467
3.500 0.5686 0.01051 0.00394 -0.0368 0.5636 0.8586
3.750 0.5938 0.01060 0.00403 -0.0361 0.5404 0.8720
4.000 0.6189 0.01073 0.00412 -0.0355 0.5121 0.8878
4.250 0.6449 0.01093 0.00425 -0.0350 0.4769 0.9070
4.500 0.6744 0.01125 0.00445 -0.0355 0.4328 0.9314
4.750 0.7071 0.01172 0.00472 -0.0369 0.3823 0.9681
5.000 0.7337 0.01228 0.00503 -0.0373 0.3330 1.0000
5.250 0.7538 0.01283 0.00538 -0.0362 0.2972 1.0000
5.500 0.7752 0.01332 0.00573 -0.0354 0.2717 1.0000
5.750 0.7970 0.01378 0.00610 -0.0346 0.2523 1.0000
6.000 0.8198 0.01418 0.00646 -0.0339 0.2349 1.0000
6.250 0.8426 0.01458 0.00685 -0.0333 0.2185 1.0000
6.500 0.8654 0.01498 0.00723 -0.0326 0.2022 1.0000
6.750 0.8875 0.01541 0.00763 -0.0318 0.1833 1.0000
7.000 0.9088 0.01591 0.00806 -0.0310 0.1600 1.0000
7.250 0.9286 0.01653 0.00855 -0.0300 0.1328 1.0000
7.500 0.9473 0.01725 0.00915 -0.0288 0.1093 1.0000
7.750 0.9662 0.01794 0.00978 -0.0277 0.0925 1.0000
8.000 0.9846 0.01865 0.01045 -0.0265 0.0801 1.0000
8.250 1.0022 0.01940 0.01116 -0.0252 0.0712 1.0000
8.500 1.0207 0.02005 0.01186 -0.0240 0.0648 1.0000
8.750 1.0363 0.02087 0.01269 -0.0224 0.0600 1.0000
9.000 1.0534 0.02155 0.01346 -0.0210 0.0566 1.0000
9.250 1.0689 0.02225 0.01424 -0.0194 0.0532 1.0000
9.500 1.0814 0.02306 0.01508 -0.0174 0.0504 1.0000
9.750 1.0912 0.02404 0.01608 -0.0152 0.0476 1.0000
10.000 1.1063 0.02473 0.01688 -0.0136 0.0451 1.0000
10.250 1.1200 0.02551 0.01774 -0.0121 0.0423 1.0000
10.500 1.1317 0.02642 0.01870 -0.0105 0.0395 1.0000
10.750 1.1395 0.02765 0.01996 -0.0086 0.0375 1.0000
11.000 1.1524 0.02856 0.02101 -0.0073 0.0361 1.0000
11.250 1.1635 0.02964 0.02222 -0.0059 0.0348 1.0000
11.500 1.1738 0.03081 0.02350 -0.0046 0.0335 1.0000
11.750 1.1845 0.03193 0.02472 -0.0035 0.0316 1.0000
12.000 1.1926 0.03330 0.02615 -0.0023 0.0300 1.0000
12.250 1.1992 0.03485 0.02777 -0.0012 0.0283 1.0000
12.500 1.2090 0.03619 0.02928 -0.0004 0.0268 1.0000
12.750 1.2183 0.03761 0.03086 0.0004 0.0249 1.0000
13.000 1.2267 0.03912 0.03246 0.0009 0.0229 1.0000
13.250 1.2314 0.04103 0.03444 0.0015 0.0212 1.0000
13.500 1.2373 0.04292 0.03651 0.0020 0.0196 1.0000
13.750 1.2434 0.04485 0.03853 0.0022 0.0173 1.0000
14.000 1.2449 0.04731 0.04107 0.0023 0.0155 1.0000
14.250 1.2453 0.05001 0.04393 0.0023 0.0141 1.0000
14.500 1.2437 0.05305 0.04710 0.0020 0.0130 1.0000
14.750 1.2394 0.05654 0.05070 0.0013 0.0122 1.0000
15.000 1.2330 0.06049 0.05478 0.0003 0.0115 1.0000
15.250 1.2254 0.06483 0.05930 -0.0011 0.0109 1.0000
15.500 1.2165 0.06960 0.06424 -0.0029 0.0104 1.0000
15.750 1.2055 0.07501 0.06982 -0.0053 0.0099 1.0000
16.000 1.1932 0.08091 0.07589 -0.0082 0.0096 1.0000
16.250 1.1792 0.08739 0.08255 -0.0115 0.0096 1.0000
16.500 1.1634 0.09457 0.08990 -0.0154 0.0094 1.0000
16.750 1.1452 0.10248 0.09798 -0.0198 0.0093 1.0000
17.000 1.1265 0.11078 0.10645 -0.0244 0.0094 1.0000
17.250 1.1069 0.11947 0.11531 -0.0293 0.0095 1.0000
17.500 1.0841 0.12918 0.12517 -0.0349 0.0095 1.0000
17.750 1.0631 0.13871 0.13486 -0.0404 0.0097 1.0000
18.000 1.0403 0.14905 0.14535 -0.0464 0.0099 1.0000
18.250 1.0159 0.16033 0.15676 -0.0529 0.0102 1.0000
18.500 0.9865 0.17373 0.17030 -0.0604 0.0104 1.0000
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