HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il) Reynolds number: 50,000 Max Cl/Cd: 34.42 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1511-il-50000-n5.txt Download as CSV file: xf-hq1511-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5228 0.09775 0.09055 -0.0302 1.0000 0.0443
-10.250 -0.5284 0.09178 0.08466 -0.0335 1.0000 0.0441
-10.000 -0.5365 0.08506 0.07798 -0.0377 1.0000 0.0437
-9.750 -0.5502 0.07830 0.07127 -0.0425 1.0000 0.0433
-9.500 -0.5662 0.07261 0.06558 -0.0463 1.0000 0.0428
-9.250 -0.5860 0.06780 0.06075 -0.0484 1.0000 0.0424
-9.000 -0.6037 0.06354 0.05638 -0.0489 1.0000 0.0423
-8.750 -0.6155 0.05944 0.05211 -0.0489 1.0000 0.0422
-8.500 -0.6239 0.05537 0.04777 -0.0483 1.0000 0.0426
-8.250 -0.6276 0.05157 0.04364 -0.0472 1.0000 0.0432
-8.000 -0.6289 0.04777 0.03938 -0.0458 1.0000 0.0446
-7.750 -0.6258 0.04436 0.03546 -0.0440 1.0000 0.0462
-7.500 -0.6152 0.04238 0.03348 -0.0427 1.0000 0.0490
-7.250 -0.6045 0.04021 0.03108 -0.0410 1.0000 0.0526
-7.000 -0.5939 0.03770 0.02790 -0.0390 1.0000 0.0575
-6.750 -0.5810 0.03612 0.02642 -0.0377 1.0000 0.0634
-6.500 -0.5666 0.03416 0.02393 -0.0358 1.0000 0.0698
-6.250 -0.5515 0.03245 0.02226 -0.0342 1.0000 0.0761
-6.000 -0.5341 0.03082 0.02027 -0.0324 1.0000 0.0825
-5.750 -0.5169 0.02933 0.01877 -0.0308 1.0000 0.0885
-5.500 -0.4993 0.02822 0.01744 -0.0290 1.0000 0.0968
-5.250 -0.4824 0.02704 0.01626 -0.0273 1.0000 0.1032
-5.000 -0.4656 0.02613 0.01521 -0.0255 1.0000 0.1132
-4.750 -0.4496 0.02522 0.01431 -0.0238 1.0000 0.1238
-4.500 -0.4334 0.02435 0.01346 -0.0223 1.0000 0.1365
-4.250 -0.4167 0.02351 0.01271 -0.0210 1.0000 0.1566
-4.000 -0.3986 0.02260 0.01192 -0.0201 1.0000 0.1893
-3.750 -0.3822 0.02141 0.01117 -0.0192 1.0000 0.2607
-3.500 -0.3586 0.02018 0.01099 -0.0193 0.9947 0.4398
-3.250 -0.3332 0.02012 0.01138 -0.0181 0.9872 0.5737
-3.000 -0.3060 0.02039 0.01163 -0.0173 0.9797 0.6515
-2.750 -0.2815 0.02076 0.01200 -0.0156 0.9720 0.7179
-2.500 -0.2597 0.02105 0.01227 -0.0131 0.9643 0.7653
-2.250 -0.2305 0.02121 0.01229 -0.0128 0.9575 0.7956
-2.000 -0.2027 0.02125 0.01214 -0.0126 0.9500 0.8174
-1.750 -0.1713 0.02135 0.01213 -0.0127 0.9435 0.8458
-1.500 -0.1401 0.02144 0.01213 -0.0127 0.9366 0.8755
-1.250 -0.0986 0.02155 0.01208 -0.0151 0.9306 0.9002
-1.000 -0.0524 0.02161 0.01198 -0.0189 0.9243 0.9163
-0.750 -0.0059 0.02164 0.01186 -0.0230 0.9166 0.9303
-0.500 0.0458 0.02167 0.01176 -0.0280 0.9101 0.9431
-0.250 0.0948 0.02169 0.01168 -0.0327 0.9023 0.9562
0.000 0.1524 0.02169 0.01158 -0.0389 0.8975 0.9665
0.250 0.1981 0.02171 0.01157 -0.0432 0.8889 0.9807
0.500 0.2513 0.02166 0.01149 -0.0486 0.8832 0.9936
0.750 0.2754 0.02173 0.01155 -0.0490 0.8721 1.0000
1.000 0.2942 0.02182 0.01163 -0.0482 0.8609 1.0000
1.250 0.3218 0.02189 0.01169 -0.0487 0.8520 1.0000
1.500 0.3423 0.02202 0.01181 -0.0479 0.8401 1.0000
1.750 0.3665 0.02207 0.01184 -0.0473 0.8262 1.0000
2.000 0.3960 0.02192 0.01171 -0.0471 0.8104 1.0000
2.250 0.4265 0.02167 0.01146 -0.0467 0.7934 1.0000
2.500 0.4488 0.02161 0.01140 -0.0453 0.7743 1.0000
2.750 0.4742 0.02158 0.01139 -0.0444 0.7585 1.0000
3.000 0.4998 0.02162 0.01150 -0.0437 0.7441 1.0000
3.250 0.5253 0.02166 0.01160 -0.0429 0.7291 1.0000
3.500 0.5505 0.02171 0.01172 -0.0420 0.7133 1.0000
3.750 0.5757 0.02176 0.01188 -0.0412 0.6966 1.0000
4.000 0.6013 0.02178 0.01199 -0.0402 0.6789 1.0000
4.250 0.6278 0.02174 0.01203 -0.0393 0.6602 1.0000
4.500 0.6501 0.02186 0.01227 -0.0379 0.6367 1.0000
4.750 0.6749 0.02188 0.01240 -0.0368 0.6127 1.0000
5.000 0.6995 0.02191 0.01250 -0.0355 0.5856 1.0000
5.250 0.7223 0.02201 0.01266 -0.0340 0.5523 1.0000
5.500 0.7456 0.02209 0.01269 -0.0324 0.5142 1.0000
5.750 0.7672 0.02236 0.01282 -0.0307 0.4728 1.0000
6.000 0.7876 0.02288 0.01317 -0.0290 0.4333 1.0000
6.250 0.8070 0.02354 0.01373 -0.0276 0.3970 1.0000
6.500 0.8256 0.02428 0.01443 -0.0261 0.3630 1.0000
6.750 0.8434 0.02508 0.01516 -0.0247 0.3311 1.0000
7.000 0.8602 0.02600 0.01597 -0.0232 0.3010 1.0000
7.250 0.8762 0.02703 0.01694 -0.0217 0.2709 1.0000
7.500 0.8909 0.02814 0.01801 -0.0201 0.2401 1.0000
7.750 0.9044 0.02934 0.01920 -0.0185 0.2096 1.0000
8.000 0.9172 0.03057 0.02043 -0.0169 0.1792 1.0000
8.250 0.9288 0.03183 0.02163 -0.0152 0.1522 1.0000
8.500 0.9396 0.03331 0.02297 -0.0136 0.1316 1.0000
8.750 0.9517 0.03498 0.02458 -0.0121 0.1144 1.0000
9.000 0.9641 0.03673 0.02633 -0.0106 0.1005 1.0000
9.250 0.9785 0.03857 0.02821 -0.0093 0.0906 1.0000
9.500 0.9913 0.04041 0.03009 -0.0080 0.0821 1.0000
9.750 1.0071 0.04244 0.03238 -0.0069 0.0746 1.0000
10.000 1.0227 0.04451 0.03446 -0.0059 0.0696 1.0000
10.250 1.0365 0.04694 0.03721 -0.0048 0.0649 1.0000
10.500 1.0451 0.04922 0.03973 -0.0034 0.0609 1.0000
10.750 1.0552 0.05154 0.04213 -0.0023 0.0580 1.0000
11.000 1.0645 0.05461 0.04539 -0.0013 0.0561 1.0000
11.250 1.0615 0.05797 0.04922 0.0002 0.0547 1.0000
11.500 1.0541 0.06153 0.05315 0.0014 0.0535 1.0000
11.750 1.0432 0.06542 0.05734 0.0020 0.0524 1.0000
12.000 1.0294 0.06971 0.06191 0.0019 0.0517 1.0000
12.250 1.0121 0.07469 0.06714 0.0008 0.0512 1.0000
12.500 0.9904 0.08067 0.07336 -0.0014 0.0513 1.0000
12.750 0.9630 0.08821 0.08108 -0.0053 0.0518 1.0000
13.000 0.9317 0.09761 0.09065 -0.0110 0.0529 1.0000
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Polar data table (+)
Polar graphs
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