HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.4 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1511-il-1000000.txt Download as CSV file: xf-hq1511-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.5/11 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7485 0.08496 0.08310 -0.0283 1.0000 0.0071
-13.250 -0.7536 0.07882 0.07691 -0.0317 1.0000 0.0070
-13.000 -0.7829 0.06633 0.06427 -0.0404 1.0000 0.0070
-12.750 -0.8037 0.05716 0.05494 -0.0479 1.0000 0.0070
-12.500 -0.8069 0.05256 0.05025 -0.0516 1.0000 0.0069
-12.250 -0.8374 0.04474 0.04221 -0.0572 1.0000 0.0070
-12.000 -0.8438 0.04131 0.03866 -0.0589 1.0000 0.0069
-11.750 -0.8506 0.03832 0.03553 -0.0596 1.0000 0.0069
-11.500 -0.8561 0.03596 0.03306 -0.0592 1.0000 0.0069
-11.250 -0.8782 0.03289 0.02978 -0.0562 1.0000 0.0069
-11.000 -0.8899 0.02966 0.02628 -0.0534 1.0000 0.0068
-10.750 -0.8824 0.02804 0.02448 -0.0518 1.0000 0.0069
-10.500 -0.8766 0.02599 0.02219 -0.0499 1.0000 0.0069
-10.250 -0.8720 0.02351 0.01944 -0.0476 1.0000 0.0070
-10.000 -0.8652 0.02127 0.01695 -0.0453 1.0000 0.0071
-9.750 -0.8536 0.01980 0.01532 -0.0433 1.0000 0.0071
-9.500 -0.8422 0.01862 0.01401 -0.0409 1.0000 0.0072
-9.250 -0.8131 0.01720 0.01245 -0.0423 0.9972 0.0074
-9.000 -0.7819 0.01610 0.01123 -0.0438 0.9933 0.0076
-8.750 -0.7512 0.01519 0.01023 -0.0450 0.9888 0.0077
-8.500 -0.7186 0.01434 0.00928 -0.0466 0.9853 0.0078
-8.250 -0.6860 0.01361 0.00847 -0.0481 0.9810 0.0079
-8.000 -0.6541 0.01293 0.00772 -0.0493 0.9746 0.0081
-7.750 -0.6217 0.01233 0.00704 -0.0506 0.9681 0.0082
-7.500 -0.5923 0.01180 0.00644 -0.0512 0.9586 0.0083
-7.250 -0.5659 0.01136 0.00593 -0.0510 0.9470 0.0086
-7.000 -0.5405 0.01098 0.00548 -0.0506 0.9350 0.0088
-6.750 -0.5155 0.01063 0.00504 -0.0501 0.9227 0.0090
-6.500 -0.4904 0.01030 0.00463 -0.0495 0.9106 0.0092
-6.250 -0.4650 0.01002 0.00426 -0.0490 0.8987 0.0094
-6.000 -0.4393 0.00972 0.00389 -0.0485 0.8876 0.0103
-5.750 -0.4134 0.00945 0.00358 -0.0481 0.8775 0.0121
-5.500 -0.3878 0.00915 0.00328 -0.0477 0.8681 0.0209
-5.250 -0.3613 0.00893 0.00307 -0.0475 0.8586 0.0279
-5.000 -0.3347 0.00874 0.00288 -0.0473 0.8496 0.0347
-4.750 -0.3079 0.00858 0.00270 -0.0470 0.8400 0.0409
-4.500 -0.2807 0.00844 0.00254 -0.0469 0.8312 0.0459
-4.250 -0.2538 0.00827 0.00237 -0.0468 0.8232 0.0551
-4.000 -0.2264 0.00809 0.00222 -0.0467 0.8150 0.0645
-3.750 -0.1992 0.00793 0.00205 -0.0466 0.8077 0.0768
-3.500 -0.1720 0.00770 0.00189 -0.0465 0.7999 0.0987
-3.250 -0.1463 0.00725 0.00169 -0.0463 0.7924 0.1692
-3.000 -0.1193 0.00700 0.00156 -0.0463 0.7839 0.2126
-2.750 -0.0928 0.00667 0.00141 -0.0462 0.7763 0.2678
-2.500 -0.0680 0.00603 0.00123 -0.0460 0.7684 0.4070
-2.250 -0.0416 0.00572 0.00114 -0.0458 0.7614 0.4806
-2.000 -0.0143 0.00553 0.00109 -0.0457 0.7546 0.5304
-1.750 0.0132 0.00544 0.00106 -0.0456 0.7483 0.5690
-1.500 0.0411 0.00537 0.00105 -0.0456 0.7410 0.5998
-1.250 0.0689 0.00535 0.00104 -0.0455 0.7335 0.6207
-1.000 0.0971 0.00533 0.00103 -0.0454 0.7245 0.6393
-0.750 0.1251 0.00534 0.00104 -0.0454 0.7162 0.6574
-0.500 0.1531 0.00534 0.00104 -0.0453 0.7080 0.6718
-0.250 0.1813 0.00535 0.00104 -0.0453 0.7002 0.6803
0.000 0.2096 0.00537 0.00104 -0.0453 0.6923 0.6893
0.250 0.2378 0.00538 0.00106 -0.0453 0.6847 0.6980
0.500 0.2659 0.00541 0.00107 -0.0453 0.6757 0.7061
0.750 0.2942 0.00541 0.00109 -0.0453 0.6666 0.7137
1.000 0.3223 0.00545 0.00110 -0.0453 0.6574 0.7206
1.250 0.3503 0.00547 0.00113 -0.0452 0.6469 0.7275
1.500 0.3786 0.00551 0.00115 -0.0453 0.6358 0.7340
1.750 0.4064 0.00554 0.00119 -0.0452 0.6232 0.7404
2.000 0.4343 0.00560 0.00123 -0.0451 0.6084 0.7476
2.250 0.4614 0.00568 0.00128 -0.0449 0.5871 0.7552
2.500 0.4879 0.00585 0.00133 -0.0447 0.5494 0.7631
2.750 0.5129 0.00613 0.00144 -0.0442 0.4963 0.7704
3.000 0.5381 0.00644 0.00158 -0.0437 0.4512 0.7784
3.250 0.5638 0.00667 0.00172 -0.0434 0.4169 0.7872
3.500 0.5895 0.00692 0.00187 -0.0431 0.3787 0.7969
3.750 0.6134 0.00735 0.00206 -0.0425 0.3156 0.8079
4.000 0.6384 0.00763 0.00226 -0.0420 0.2848 0.8198
4.250 0.6640 0.00783 0.00243 -0.0416 0.2657 0.8336
4.500 0.6894 0.00799 0.00260 -0.0412 0.2503 0.8504
4.750 0.7142 0.00813 0.00277 -0.0406 0.2359 0.8709
5.000 0.7378 0.00825 0.00294 -0.0397 0.2216 0.9019
5.250 0.7661 0.00831 0.00311 -0.0398 0.2106 0.9571
5.500 0.8041 0.00854 0.00330 -0.0422 0.1952 1.0000
5.750 0.8298 0.00879 0.00348 -0.0420 0.1760 1.0000
6.000 0.8530 0.00929 0.00376 -0.0414 0.1344 1.0000
6.250 0.8763 0.00978 0.00410 -0.0408 0.1068 1.0000
6.500 0.9004 0.01018 0.00442 -0.0403 0.0891 1.0000
6.750 0.9246 0.01056 0.00474 -0.0398 0.0750 1.0000
7.000 0.9486 0.01096 0.00507 -0.0393 0.0617 1.0000
7.250 0.9718 0.01143 0.00545 -0.0387 0.0474 1.0000
7.500 0.9948 0.01192 0.00586 -0.0380 0.0352 1.0000
7.750 1.0174 0.01244 0.00633 -0.0373 0.0278 1.0000
8.000 1.0411 0.01283 0.00673 -0.0367 0.0249 1.0000
8.250 1.0625 0.01346 0.00738 -0.0357 0.0214 1.0000
8.500 1.0862 0.01381 0.00778 -0.0352 0.0204 1.0000
8.750 1.1092 0.01422 0.00821 -0.0345 0.0191 1.0000
9.000 1.1308 0.01473 0.00874 -0.0337 0.0177 1.0000
9.250 1.1486 0.01560 0.00968 -0.0322 0.0162 1.0000
9.500 1.1703 0.01605 0.01019 -0.0314 0.0158 1.0000
9.750 1.1917 0.01650 0.01068 -0.0305 0.0151 1.0000
10.000 1.2124 0.01698 0.01120 -0.0296 0.0143 1.0000
10.250 1.2320 0.01752 0.01178 -0.0285 0.0136 1.0000
10.500 1.2494 0.01820 0.01249 -0.0271 0.0129 1.0000
10.750 1.2588 0.01939 0.01378 -0.0246 0.0122 1.0000
11.000 1.2718 0.02010 0.01456 -0.0225 0.0118 1.0000
11.250 1.2866 0.02062 0.01514 -0.0207 0.0115 1.0000
11.500 1.3003 0.02120 0.01579 -0.0188 0.0111 1.0000
11.750 1.3127 0.02188 0.01652 -0.0168 0.0107 1.0000
12.000 1.3249 0.02259 0.01728 -0.0150 0.0102 1.0000
12.250 1.3352 0.02344 0.01819 -0.0130 0.0099 1.0000
12.500 1.3454 0.02434 0.01914 -0.0113 0.0096 1.0000
12.750 1.3480 0.02581 0.02069 -0.0089 0.0092 1.0000
13.000 1.3375 0.02836 0.02340 -0.0059 0.0088 1.0000
13.250 1.3452 0.02967 0.02480 -0.0046 0.0087 1.0000
13.500 1.3532 0.03100 0.02622 -0.0034 0.0085 1.0000
13.750 1.3619 0.03233 0.02764 -0.0025 0.0083 1.0000
14.000 1.3686 0.03390 0.02929 -0.0016 0.0081 1.0000
14.250 1.3699 0.03604 0.03154 -0.0007 0.0079 1.0000
14.500 1.3761 0.03778 0.03336 -0.0002 0.0077 1.0000
14.750 1.3754 0.04031 0.03600 0.0003 0.0075 1.0000
15.000 1.3770 0.04271 0.03849 0.0004 0.0074 1.0000
15.250 1.3795 0.04512 0.04097 0.0003 0.0071 1.0000
15.500 1.3794 0.04792 0.04386 0.0000 0.0070 1.0000
15.750 1.3751 0.05139 0.04742 -0.0006 0.0068 1.0000
16.000 1.3659 0.05569 0.05186 -0.0018 0.0068 1.0000
16.250 1.3585 0.06005 0.05632 -0.0033 0.0067 1.0000
16.500 1.3445 0.06568 0.06207 -0.0057 0.0065 1.0000
16.750 1.3293 0.07186 0.06841 -0.0085 0.0065 1.0000
17.000 1.3060 0.07974 0.07645 -0.0125 0.0064 1.0000
17.250 1.2821 0.08809 0.08496 -0.0169 0.0063 1.0000
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