HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il) Reynolds number: 500,000 Max Cl/Cd: 67.33 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1585-il-500000-n5.txt Download as CSV file: xf-hq1585-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/8.5 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5896 0.08653 0.08431 -0.0165 1.0000 0.0059
-10.000 -0.6098 0.07773 0.07557 -0.0218 1.0000 0.0057
-9.750 -0.6290 0.06889 0.06679 -0.0281 1.0000 0.0056
-9.250 -0.7651 0.02976 0.02631 -0.0463 1.0000 0.0051
-9.000 -0.7557 0.02598 0.02206 -0.0457 1.0000 0.0054
-8.750 -0.7401 0.02344 0.01914 -0.0449 1.0000 0.0058
-8.500 -0.7210 0.02180 0.01723 -0.0443 1.0000 0.0060
-8.250 -0.7046 0.01938 0.01446 -0.0433 1.0000 0.0064
-8.000 -0.6835 0.01838 0.01329 -0.0426 1.0000 0.0068
-7.750 -0.6616 0.01770 0.01253 -0.0419 1.0000 0.0073
-7.500 -0.6345 0.01693 0.01164 -0.0422 0.9965 0.0078
-7.250 -0.6027 0.01599 0.01055 -0.0435 0.9896 0.0086
-7.000 -0.5707 0.01507 0.00946 -0.0448 0.9817 0.0094
-6.750 -0.5377 0.01449 0.00875 -0.0462 0.9734 0.0101
-6.500 -0.5054 0.01375 0.00794 -0.0476 0.9643 0.0117
-6.250 -0.4735 0.01334 0.00748 -0.0487 0.9541 0.0130
-6.000 -0.4429 0.01282 0.00686 -0.0494 0.9435 0.0143
-5.750 -0.4139 0.01239 0.00632 -0.0498 0.9322 0.0153
-5.500 -0.3865 0.01197 0.00581 -0.0498 0.9211 0.0163
-5.250 -0.3609 0.01133 0.00508 -0.0495 0.9100 0.0182
-5.000 -0.3346 0.01096 0.00465 -0.0492 0.8995 0.0195
-4.750 -0.3081 0.01067 0.00427 -0.0490 0.8900 0.0212
-4.250 -0.2548 0.01010 0.00351 -0.0485 0.8720 0.0236
-4.000 -0.2281 0.00977 0.00310 -0.0482 0.8640 0.0252
-3.750 -0.2012 0.00948 0.00276 -0.0480 0.8562 0.0288
-3.500 -0.1740 0.00927 0.00250 -0.0478 0.8492 0.0334
-3.250 -0.1469 0.00905 0.00228 -0.0477 0.8423 0.0445
-3.000 -0.1196 0.00884 0.00208 -0.0476 0.8362 0.0603
-2.750 -0.0926 0.00854 0.00188 -0.0475 0.8300 0.0941
-2.500 -0.0660 0.00815 0.00169 -0.0475 0.8244 0.1634
-2.250 -0.0389 0.00785 0.00156 -0.0475 0.8184 0.2200
-2.000 -0.0124 0.00746 0.00143 -0.0475 0.8120 0.3047
-1.750 0.0130 0.00686 0.00132 -0.0474 0.8038 0.4494
-1.500 0.0389 0.00655 0.00128 -0.0470 0.7947 0.5462
-1.250 0.0659 0.00643 0.00125 -0.0468 0.7855 0.5886
-1.000 0.0931 0.00634 0.00124 -0.0465 0.7766 0.6252
-0.750 0.1200 0.00628 0.00123 -0.0462 0.7661 0.6597
-0.500 0.1472 0.00626 0.00122 -0.0459 0.7543 0.6805
-0.250 0.1747 0.00626 0.00120 -0.0457 0.7420 0.6971
0.000 0.2023 0.00625 0.00120 -0.0455 0.7301 0.7123
0.250 0.2298 0.00625 0.00122 -0.0453 0.7186 0.7291
0.500 0.2572 0.00626 0.00123 -0.0451 0.7073 0.7453
0.750 0.2847 0.00628 0.00125 -0.0449 0.6946 0.7582
1.000 0.3119 0.00631 0.00127 -0.0447 0.6786 0.7705
1.250 0.3390 0.00635 0.00129 -0.0444 0.6608 0.7827
1.500 0.3656 0.00643 0.00131 -0.0440 0.6356 0.7936
1.750 0.3910 0.00662 0.00134 -0.0434 0.5892 0.8027
2.000 0.4152 0.00698 0.00142 -0.0428 0.5112 0.8113
2.250 0.4392 0.00741 0.00155 -0.0421 0.4336 0.8207
2.500 0.4640 0.00775 0.00171 -0.0416 0.3768 0.8311
2.750 0.4889 0.00804 0.00188 -0.0412 0.3297 0.8437
3.000 0.5140 0.00826 0.00204 -0.0407 0.2968 0.8604
3.250 0.5378 0.00852 0.00221 -0.0399 0.2551 0.8864
3.500 0.5643 0.00874 0.00239 -0.0396 0.2204 0.9324
3.750 0.5999 0.00904 0.00260 -0.0416 0.1888 1.0000
4.000 0.6253 0.00946 0.00284 -0.0413 0.1456 1.0000
4.250 0.6498 0.01003 0.00315 -0.0410 0.0964 1.0000
4.500 0.6744 0.01058 0.00350 -0.0407 0.0560 1.0000
4.750 0.7001 0.01096 0.00381 -0.0404 0.0435 1.0000
5.000 0.7261 0.01129 0.00415 -0.0401 0.0384 1.0000
5.250 0.7523 0.01157 0.00447 -0.0399 0.0356 1.0000
5.500 0.7785 0.01185 0.00479 -0.0397 0.0336 1.0000
5.750 0.8045 0.01216 0.00513 -0.0395 0.0321 1.0000
6.000 0.8300 0.01252 0.00549 -0.0392 0.0290 1.0000
6.250 0.8550 0.01296 0.00596 -0.0388 0.0253 1.0000
6.500 0.8811 0.01320 0.00627 -0.0386 0.0236 1.0000
6.750 0.9069 0.01347 0.00658 -0.0384 0.0203 1.0000
7.000 0.9319 0.01387 0.00695 -0.0381 0.0139 1.0000
7.250 0.9556 0.01445 0.00746 -0.0376 0.0094 1.0000
7.500 0.9790 0.01510 0.00815 -0.0370 0.0073 1.0000
7.750 1.0025 0.01570 0.00883 -0.0364 0.0066 1.0000
8.000 1.0258 0.01631 0.00954 -0.0358 0.0060 1.0000
8.250 1.0484 0.01699 0.01035 -0.0351 0.0057 1.0000
8.500 1.0704 0.01774 0.01121 -0.0344 0.0053 1.0000
8.750 1.0917 0.01857 0.01214 -0.0335 0.0050 1.0000
9.000 1.1121 0.01948 0.01317 -0.0326 0.0047 1.0000
9.250 1.1311 0.02055 0.01437 -0.0316 0.0045 1.0000
9.500 1.1473 0.02196 0.01594 -0.0302 0.0042 1.0000
9.750 1.1587 0.02399 0.01821 -0.0282 0.0039 1.0000
10.000 1.1743 0.02533 0.01971 -0.0268 0.0039 1.0000
10.250 1.1895 0.02662 0.02116 -0.0255 0.0038 1.0000
10.500 1.2033 0.02796 0.02271 -0.0240 0.0037 1.0000
10.750 1.2158 0.02932 0.02425 -0.0224 0.0036 1.0000
11.000 1.2250 0.03084 0.02594 -0.0205 0.0035 1.0000
11.250 1.2286 0.03246 0.02775 -0.0179 0.0034 1.0000
11.500 1.2316 0.03400 0.02946 -0.0154 0.0032 1.0000
11.750 1.2298 0.03605 0.03169 -0.0130 0.0032 1.0000
12.000 1.2281 0.03818 0.03400 -0.0112 0.0031 1.0000
12.250 1.2222 0.04092 0.03694 -0.0098 0.0030 1.0000
12.500 1.2139 0.04415 0.04038 -0.0090 0.0030 1.0000
12.750 1.2046 0.04777 0.04418 -0.0090 0.0030 1.0000
13.000 1.1902 0.05245 0.04908 -0.0099 0.0030 1.0000
13.250 1.1759 0.05770 0.05452 -0.0120 0.0030 1.0000
13.500 1.1597 0.06395 0.06095 -0.0153 0.0030 1.0000
13.750 1.1399 0.07181 0.06901 -0.0203 0.0030 1.0000
14.000 1.1201 0.08078 0.07816 -0.0263 0.0030 1.0000
14.250 1.0900 0.09309 0.09066 -0.0343 0.0031 1.0000
14.500 1.0529 0.10760 0.10532 -0.0429 0.0032 1.0000
14.750 1.0250 0.12013 0.11795 -0.0498 0.0032 1.0000
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Polar data table (+)
Polar graphs
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