HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il) Reynolds number: 100,000 Max Cl/Cd: 49.15 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1510-il-100000-n5.txt Download as CSV file: xf-hq1510-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/10 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5222 0.09158 0.08661 -0.0256 1.0000 0.0211
-9.750 -0.5272 0.08598 0.08107 -0.0287 1.0000 0.0208
-9.500 -0.5347 0.07961 0.07476 -0.0326 1.0000 0.0207
-9.250 -0.5461 0.07162 0.06683 -0.0387 1.0000 0.0202
-9.000 -0.5641 0.06461 0.05980 -0.0442 1.0000 0.0197
-8.750 -0.5848 0.05949 0.05461 -0.0462 1.0000 0.0195
-8.500 -0.5993 0.05448 0.04941 -0.0470 1.0000 0.0194
-8.250 -0.6076 0.04986 0.04454 -0.0469 1.0000 0.0193
-8.000 -0.6111 0.04557 0.03991 -0.0461 1.0000 0.0196
-7.750 -0.6095 0.04179 0.03576 -0.0448 1.0000 0.0201
-7.500 -0.6042 0.03842 0.03195 -0.0432 1.0000 0.0215
-7.250 -0.5958 0.03528 0.02828 -0.0413 1.0000 0.0227
-7.000 -0.5843 0.03260 0.02511 -0.0394 1.0000 0.0234
-6.750 -0.5724 0.02968 0.02187 -0.0376 1.0000 0.0241
-6.500 -0.5582 0.02770 0.01970 -0.0359 1.0000 0.0252
-6.250 -0.5425 0.02616 0.01798 -0.0342 1.0000 0.0267
-6.000 -0.5260 0.02475 0.01637 -0.0325 1.0000 0.0288
-5.750 -0.5087 0.02365 0.01501 -0.0308 1.0000 0.0324
-5.500 -0.4914 0.02232 0.01355 -0.0294 0.9998 0.0359
-5.250 -0.4582 0.02100 0.01213 -0.0309 0.9943 0.0420
-5.000 -0.4257 0.01998 0.01105 -0.0323 0.9881 0.0520
-4.750 -0.3925 0.01907 0.01007 -0.0339 0.9825 0.0644
-4.500 -0.3604 0.01829 0.00924 -0.0353 0.9759 0.0788
-4.250 -0.3264 0.01751 0.00842 -0.0369 0.9705 0.0943
-4.000 -0.2956 0.01679 0.00771 -0.0379 0.9633 0.1165
-3.750 -0.2613 0.01596 0.00711 -0.0398 0.9582 0.1675
-3.500 -0.2328 0.01503 0.00663 -0.0407 0.9508 0.2698
-3.250 -0.2035 0.01401 0.00645 -0.0417 0.9451 0.4581
-3.000 -0.1761 0.01374 0.00648 -0.0413 0.9376 0.5658
-2.750 -0.1446 0.01368 0.00647 -0.0416 0.9314 0.6287
-2.500 -0.1165 0.01368 0.00648 -0.0413 0.9238 0.6740
-2.250 -0.0863 0.01370 0.00652 -0.0411 0.9175 0.7148
-2.000 -0.0589 0.01373 0.00649 -0.0405 0.9098 0.7437
-1.750 -0.0277 0.01370 0.00639 -0.0407 0.9035 0.7641
-1.500 -0.0008 0.01369 0.00635 -0.0401 0.8954 0.7857
-1.250 0.0289 0.01364 0.00627 -0.0399 0.8890 0.8063
-1.000 0.0555 0.01361 0.00618 -0.0394 0.8802 0.8218
-0.750 0.0872 0.01353 0.00603 -0.0399 0.8739 0.8344
-0.500 0.1138 0.01349 0.00596 -0.0394 0.8645 0.8473
-0.250 0.1432 0.01342 0.00585 -0.0395 0.8568 0.8602
0.000 0.1723 0.01337 0.00578 -0.0395 0.8484 0.8736
0.250 0.2014 0.01333 0.00574 -0.0395 0.8396 0.8878
0.500 0.2342 0.01325 0.00566 -0.0401 0.8322 0.9018
0.750 0.2668 0.01321 0.00564 -0.0409 0.8214 0.9166
1.000 0.3023 0.01313 0.00555 -0.0421 0.8091 0.9318
1.250 0.3391 0.01302 0.00544 -0.0436 0.7948 0.9484
1.500 0.3766 0.01291 0.00531 -0.0453 0.7794 0.9661
1.750 0.4145 0.01283 0.00523 -0.0473 0.7646 0.9863
2.000 0.4449 0.01283 0.00524 -0.0480 0.7509 1.0000
2.250 0.4670 0.01289 0.00528 -0.0470 0.7374 1.0000
2.500 0.4906 0.01295 0.00534 -0.0461 0.7230 1.0000
2.750 0.5149 0.01302 0.00541 -0.0454 0.7079 1.0000
3.000 0.5398 0.01309 0.00547 -0.0447 0.6916 1.0000
3.250 0.5644 0.01320 0.00562 -0.0439 0.6730 1.0000
3.500 0.5892 0.01329 0.00573 -0.0432 0.6525 1.0000
3.750 0.6138 0.01341 0.00585 -0.0423 0.6291 1.0000
4.000 0.6381 0.01355 0.00599 -0.0414 0.6013 1.0000
4.250 0.6621 0.01373 0.00615 -0.0404 0.5672 1.0000
4.500 0.6851 0.01399 0.00628 -0.0393 0.5237 1.0000
4.750 0.7068 0.01438 0.00647 -0.0380 0.4699 1.0000
5.000 0.7272 0.01494 0.00676 -0.0366 0.4122 1.0000
5.250 0.7473 0.01560 0.00719 -0.0354 0.3573 1.0000
5.500 0.7676 0.01629 0.00767 -0.0343 0.3112 1.0000
5.750 0.7881 0.01700 0.00821 -0.0333 0.2732 1.0000
6.000 0.8090 0.01770 0.00880 -0.0324 0.2402 1.0000
6.250 0.8306 0.01835 0.00942 -0.0316 0.2086 1.0000
6.500 0.8513 0.01908 0.01006 -0.0307 0.1732 1.0000
6.750 0.8708 0.01998 0.01083 -0.0297 0.1341 1.0000
7.000 0.8892 0.02102 0.01171 -0.0286 0.1069 1.0000
7.250 0.9076 0.02209 0.01272 -0.0274 0.0919 1.0000
7.500 0.9261 0.02313 0.01380 -0.0262 0.0811 1.0000
7.750 0.9448 0.02415 0.01490 -0.0250 0.0723 1.0000
8.000 0.9614 0.02536 0.01611 -0.0237 0.0660 1.0000
8.250 0.9798 0.02648 0.01742 -0.0225 0.0613 1.0000
8.500 0.9971 0.02773 0.01877 -0.0212 0.0572 1.0000
8.750 1.0134 0.02915 0.02032 -0.0199 0.0524 1.0000
9.000 1.0304 0.03006 0.02141 -0.0189 0.0453 1.0000
9.250 1.0452 0.03122 0.02271 -0.0176 0.0390 1.0000
9.500 1.0592 0.03218 0.02378 -0.0164 0.0328 1.0000
9.750 1.0710 0.03382 0.02563 -0.0148 0.0281 1.0000
10.000 1.0801 0.03547 0.02745 -0.0128 0.0243 1.0000
10.250 1.0835 0.03742 0.02948 -0.0105 0.0221 1.0000
10.500 1.0898 0.03987 0.03222 -0.0085 0.0201 1.0000
10.750 1.0942 0.04230 0.03493 -0.0065 0.0185 1.0000
11.000 1.0958 0.04449 0.03733 -0.0048 0.0171 1.0000
11.250 1.0957 0.04676 0.03976 -0.0034 0.0162 1.0000
11.500 1.0935 0.04904 0.04221 -0.0025 0.0153 1.0000
11.750 1.0866 0.05230 0.04561 -0.0018 0.0146 1.0000
12.000 1.0797 0.05598 0.04961 -0.0015 0.0142 1.0000
12.250 1.0696 0.06017 0.05409 -0.0018 0.0139 1.0000
12.500 1.0575 0.06486 0.05904 -0.0029 0.0138 1.0000
12.750 1.0416 0.07044 0.06487 -0.0050 0.0136 1.0000
13.000 1.0250 0.07659 0.07124 -0.0081 0.0136 1.0000
13.250 1.0044 0.08414 0.07902 -0.0126 0.0136 1.0000
13.500 0.9861 0.09191 0.08693 -0.0174 0.0140 1.0000
13.750 0.9646 0.10123 0.09640 -0.0235 0.0142 1.0000
14.000 0.9451 0.11066 0.10586 -0.0293 0.0146 1.0000
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