HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il) Reynolds number: 200,000 Max Cl/Cd: 61.95 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1510-il-200000-n5.txt Download as CSV file: xf-hq1510-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6037 0.06028 0.05684 -0.0437 1.0000 0.0101
-9.500 -0.6278 0.05359 0.05001 -0.0487 1.0000 0.0100
-9.250 -0.6486 0.04938 0.04566 -0.0491 1.0000 0.0099
-9.000 -0.6636 0.04452 0.04052 -0.0489 1.0000 0.0099
-8.750 -0.6729 0.03967 0.03525 -0.0478 1.0000 0.0100
-8.500 -0.6730 0.03582 0.03090 -0.0462 1.0000 0.0105
-8.250 -0.6694 0.03238 0.02705 -0.0444 1.0000 0.0106
-8.000 -0.6637 0.02903 0.02329 -0.0424 1.0000 0.0109
-7.750 -0.6525 0.02675 0.02072 -0.0406 1.0000 0.0112
-7.500 -0.6391 0.02507 0.01883 -0.0389 1.0000 0.0117
-7.250 -0.6249 0.02365 0.01716 -0.0370 1.0000 0.0122
-7.000 -0.5972 0.02202 0.01528 -0.0377 0.9959 0.0129
-6.750 -0.5662 0.02045 0.01347 -0.0390 0.9904 0.0139
-6.500 -0.5332 0.01940 0.01220 -0.0404 0.9854 0.0157
-6.250 -0.5028 0.01808 0.01079 -0.0416 0.9796 0.0178
-6.000 -0.4702 0.01711 0.00972 -0.0430 0.9743 0.0199
-5.750 -0.4382 0.01620 0.00864 -0.0441 0.9686 0.0226
-5.500 -0.4075 0.01537 0.00777 -0.0451 0.9618 0.0280
-5.250 -0.3745 0.01472 0.00706 -0.0465 0.9564 0.0363
-5.000 -0.3443 0.01426 0.00653 -0.0471 0.9484 0.0447
-4.750 -0.3119 0.01378 0.00604 -0.0484 0.9425 0.0561
-4.500 -0.2828 0.01333 0.00559 -0.0489 0.9340 0.0684
-4.250 -0.2522 0.01286 0.00508 -0.0496 0.9271 0.0813
-4.000 -0.2229 0.01244 0.00465 -0.0500 0.9192 0.0987
-3.750 -0.1945 0.01194 0.00428 -0.0504 0.9116 0.1345
-3.500 -0.1671 0.01134 0.00395 -0.0506 0.9039 0.2058
-3.250 -0.1413 0.01077 0.00364 -0.0506 0.8954 0.2873
-3.000 -0.1164 0.01008 0.00343 -0.0503 0.8881 0.4166
-2.750 -0.0922 0.00972 0.00338 -0.0496 0.8790 0.5122
-2.500 -0.0660 0.00955 0.00334 -0.0490 0.8715 0.5720
-2.250 -0.0397 0.00947 0.00329 -0.0485 0.8632 0.6116
-2.000 -0.0134 0.00943 0.00327 -0.0479 0.8553 0.6470
-1.750 0.0126 0.00940 0.00328 -0.0471 0.8475 0.6792
-1.500 0.0389 0.00939 0.00326 -0.0466 0.8388 0.7002
-1.250 0.0659 0.00938 0.00319 -0.0461 0.8312 0.7157
-1.000 0.0922 0.00937 0.00318 -0.0456 0.8220 0.7328
-0.750 0.1184 0.00936 0.00317 -0.0450 0.8137 0.7491
-0.500 0.1450 0.00935 0.00313 -0.0445 0.8053 0.7628
-0.250 0.1717 0.00933 0.00310 -0.0440 0.7952 0.7735
0.000 0.1981 0.00931 0.00305 -0.0435 0.7840 0.7827
0.250 0.2246 0.00929 0.00299 -0.0430 0.7714 0.7926
0.750 0.2774 0.00926 0.00292 -0.0419 0.7476 0.8134
1.000 0.3036 0.00924 0.00290 -0.0414 0.7346 0.8244
1.250 0.3298 0.00923 0.00290 -0.0408 0.7213 0.8361
1.500 0.3561 0.00922 0.00291 -0.0403 0.7090 0.8486
1.750 0.3826 0.00922 0.00294 -0.0398 0.6967 0.8621
2.000 0.4095 0.00922 0.00296 -0.0394 0.6834 0.8771
2.250 0.4371 0.00923 0.00302 -0.0392 0.6693 0.8945
2.500 0.4669 0.00925 0.00306 -0.0394 0.6533 0.9145
2.750 0.5008 0.00930 0.00311 -0.0405 0.6349 0.9391
3.000 0.5370 0.00937 0.00320 -0.0423 0.6119 0.9700
3.250 0.5698 0.00949 0.00327 -0.0434 0.5848 1.0000
3.500 0.5941 0.00969 0.00337 -0.0427 0.5532 1.0000
3.750 0.6176 0.00997 0.00349 -0.0419 0.5119 1.0000
4.000 0.6399 0.01037 0.00365 -0.0410 0.4594 1.0000
4.250 0.6612 0.01089 0.00391 -0.0399 0.3998 1.0000
4.500 0.6825 0.01148 0.00422 -0.0390 0.3412 1.0000
4.750 0.7044 0.01205 0.00456 -0.0382 0.2947 1.0000
5.000 0.7273 0.01255 0.00492 -0.0375 0.2630 1.0000
5.250 0.7509 0.01300 0.00532 -0.0370 0.2397 1.0000
5.500 0.7748 0.01342 0.00571 -0.0365 0.2173 1.0000
5.750 0.7983 0.01388 0.00610 -0.0359 0.1894 1.0000
6.000 0.8209 0.01445 0.00653 -0.0353 0.1535 1.0000
6.250 0.8424 0.01513 0.00704 -0.0346 0.1191 1.0000
6.500 0.8637 0.01586 0.00764 -0.0338 0.0925 1.0000
6.750 0.8854 0.01654 0.00830 -0.0330 0.0752 1.0000
7.000 0.9070 0.01722 0.00897 -0.0322 0.0643 1.0000
7.250 0.9284 0.01791 0.00966 -0.0314 0.0556 1.0000
7.500 0.9504 0.01850 0.01033 -0.0307 0.0492 1.0000
7.750 0.9711 0.01923 0.01106 -0.0298 0.0434 1.0000
8.000 0.9924 0.01985 0.01179 -0.0290 0.0395 1.0000
8.250 1.0137 0.02045 0.01248 -0.0282 0.0342 1.0000
8.500 1.0334 0.02122 0.01330 -0.0273 0.0304 1.0000
8.750 1.0544 0.02182 0.01405 -0.0264 0.0263 1.0000
9.000 1.0740 0.02256 0.01478 -0.0255 0.0203 1.0000
9.250 1.0924 0.02340 0.01564 -0.0245 0.0150 1.0000
9.500 1.1087 0.02442 0.01679 -0.0231 0.0119 1.0000
9.750 1.1230 0.02561 0.01805 -0.0215 0.0099 1.0000
10.000 1.1353 0.02691 0.01948 -0.0197 0.0089 1.0000
10.250 1.1459 0.02818 0.02092 -0.0176 0.0083 1.0000
10.500 1.1540 0.02951 0.02246 -0.0153 0.0078 1.0000
10.750 1.1609 0.03092 0.02402 -0.0131 0.0075 1.0000
11.000 1.1663 0.03248 0.02574 -0.0109 0.0071 1.0000
11.250 1.1703 0.03418 0.02761 -0.0089 0.0069 1.0000
11.500 1.1728 0.03607 0.02966 -0.0071 0.0067 1.0000
11.750 1.1731 0.03822 0.03199 -0.0055 0.0065 1.0000
12.000 1.1717 0.04066 0.03460 -0.0042 0.0064 1.0000
12.250 1.1679 0.04346 0.03758 -0.0032 0.0063 1.0000
12.500 1.1634 0.04650 0.04082 -0.0027 0.0062 1.0000
12.750 1.1552 0.05019 0.04470 -0.0026 0.0061 1.0000
13.000 1.1463 0.05419 0.04890 -0.0031 0.0061 1.0000
13.250 1.1348 0.05888 0.05380 -0.0043 0.0060 1.0000
13.500 1.1247 0.06364 0.05876 -0.0061 0.0061 1.0000
13.750 1.1110 0.06938 0.06470 -0.0087 0.0060 1.0000
14.000 1.0969 0.07564 0.07116 -0.0120 0.0060 1.0000
14.250 1.0817 0.08266 0.07839 -0.0161 0.0060 1.0000
14.500 1.0634 0.09084 0.08674 -0.0210 0.0060 1.0000
14.750 1.0470 0.09916 0.09525 -0.0261 0.0061 1.0000
15.000 1.0282 0.10858 0.10484 -0.0318 0.0062 1.0000
15.250 1.0082 0.11868 0.11510 -0.0378 0.0063 1.0000
15.500 0.9777 0.13215 0.12874 -0.0454 0.0065 1.0000
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