HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il) Reynolds number: 500,000 Max Cl/Cd: 82.23 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq1511-il-500000.txt Download as CSV file: xf-hq1511-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4572 0.09740 0.09524 -0.0252 1.0000 0.0170
-11.500 -0.6682 0.06539 0.06297 -0.0432 1.0000 0.0121
-11.250 -0.6950 0.05608 0.05352 -0.0513 1.0000 0.0120
-11.000 -0.7166 0.05006 0.04735 -0.0556 1.0000 0.0119
-10.750 -0.7424 0.04485 0.04195 -0.0578 1.0000 0.0118
-10.500 -0.7658 0.04122 0.03812 -0.0566 1.0000 0.0117
-10.250 -0.7856 0.03737 0.03399 -0.0541 1.0000 0.0116
-10.000 -0.7964 0.03334 0.02958 -0.0517 1.0000 0.0115
-9.750 -0.7989 0.02983 0.02568 -0.0494 1.0000 0.0114
-9.500 -0.7938 0.02721 0.02274 -0.0472 1.0000 0.0114
-9.250 -0.7852 0.02508 0.02032 -0.0450 1.0000 0.0115
-9.000 -0.7748 0.02338 0.01839 -0.0427 1.0000 0.0116
-8.750 -0.7651 0.02197 0.01680 -0.0401 1.0000 0.0117
-8.500 -0.7536 0.02065 0.01532 -0.0378 0.9996 0.0118
-8.250 -0.7205 0.01916 0.01362 -0.0397 0.9962 0.0119
-8.000 -0.6868 0.01802 0.01232 -0.0415 0.9925 0.0123
-7.750 -0.6536 0.01699 0.01115 -0.0432 0.9881 0.0126
-7.500 -0.6207 0.01551 0.00956 -0.0451 0.9846 0.0131
-7.250 -0.5873 0.01458 0.00856 -0.0467 0.9805 0.0135
-7.000 -0.5535 0.01382 0.00774 -0.0483 0.9757 0.0141
-6.750 -0.5185 0.01315 0.00699 -0.0501 0.9716 0.0150
-6.500 -0.4861 0.01259 0.00635 -0.0513 0.9651 0.0164
-6.250 -0.4546 0.01191 0.00566 -0.0523 0.9585 0.0203
-6.000 -0.4259 0.01141 0.00519 -0.0526 0.9497 0.0302
-5.750 -0.3964 0.01119 0.00493 -0.0529 0.9419 0.0367
-5.500 -0.3709 0.01093 0.00469 -0.0525 0.9311 0.0429
-5.250 -0.3445 0.01074 0.00443 -0.0522 0.9216 0.0469
-5.000 -0.3189 0.01044 0.00412 -0.0517 0.9127 0.0532
-4.750 -0.2932 0.01023 0.00387 -0.0512 0.9024 0.0602
-4.500 -0.2674 0.01000 0.00363 -0.0508 0.8929 0.0696
-4.250 -0.2419 0.00971 0.00334 -0.0503 0.8838 0.0822
-4.000 -0.2162 0.00940 0.00307 -0.0499 0.8746 0.1023
-3.750 -0.1920 0.00885 0.00279 -0.0495 0.8662 0.1754
-3.500 -0.1676 0.00834 0.00256 -0.0491 0.8562 0.2533
-3.250 -0.1442 0.00765 0.00232 -0.0486 0.8470 0.3772
-3.000 -0.1197 0.00723 0.00217 -0.0481 0.8388 0.4737
-2.750 -0.0941 0.00696 0.00213 -0.0476 0.8305 0.5427
-2.500 -0.0673 0.00689 0.00209 -0.0473 0.8235 0.5826
-2.250 -0.0401 0.00683 0.00207 -0.0470 0.8154 0.6127
-2.000 -0.0129 0.00681 0.00205 -0.0467 0.8088 0.6379
-1.750 0.0147 0.00680 0.00204 -0.0465 0.8008 0.6565
-1.500 0.0423 0.00682 0.00202 -0.0463 0.7943 0.6738
-1.250 0.0698 0.00681 0.00203 -0.0460 0.7872 0.6903
-1.000 0.0972 0.00682 0.00203 -0.0457 0.7804 0.7056
-0.750 0.1250 0.00683 0.00202 -0.0456 0.7727 0.7160
-0.500 0.1525 0.00682 0.00199 -0.0454 0.7648 0.7247
-0.250 0.1802 0.00682 0.00198 -0.0452 0.7556 0.7349
0.000 0.2077 0.00684 0.00197 -0.0449 0.7479 0.7445
0.250 0.2354 0.00682 0.00197 -0.0448 0.7393 0.7522
0.500 0.2631 0.00684 0.00197 -0.0447 0.7311 0.7605
0.750 0.2907 0.00684 0.00197 -0.0445 0.7221 0.7681
1.000 0.3184 0.00685 0.00199 -0.0443 0.7127 0.7762
1.250 0.3458 0.00687 0.00200 -0.0441 0.7041 0.7838
1.500 0.3735 0.00689 0.00203 -0.0440 0.6942 0.7929
1.750 0.4007 0.00689 0.00207 -0.0437 0.6847 0.8007
2.000 0.4281 0.00692 0.00209 -0.0436 0.6746 0.8093
2.250 0.4552 0.00692 0.00214 -0.0433 0.6628 0.8184
2.500 0.4822 0.00693 0.00218 -0.0430 0.6502 0.8279
2.750 0.5089 0.00696 0.00223 -0.0427 0.6350 0.8385
3.000 0.5347 0.00700 0.00226 -0.0421 0.6130 0.8493
3.250 0.5597 0.00708 0.00230 -0.0414 0.5807 0.8617
3.500 0.5831 0.00722 0.00237 -0.0404 0.5383 0.8781
3.750 0.6051 0.00744 0.00248 -0.0391 0.4922 0.8994
4.000 0.6277 0.00771 0.00264 -0.0380 0.4508 0.9290
4.250 0.6611 0.00804 0.00285 -0.0394 0.4065 0.9633
4.500 0.6974 0.00853 0.00310 -0.0417 0.3408 1.0000
4.750 0.7208 0.00899 0.00335 -0.0412 0.3045 1.0000
5.000 0.7452 0.00937 0.00361 -0.0408 0.2813 1.0000
5.250 0.7698 0.00972 0.00388 -0.0404 0.2608 1.0000
5.500 0.7948 0.01004 0.00413 -0.0400 0.2423 1.0000
5.750 0.8198 0.01034 0.00439 -0.0397 0.2266 1.0000
6.000 0.8447 0.01066 0.00465 -0.0393 0.2101 1.0000
6.250 0.8692 0.01100 0.00494 -0.0389 0.1896 1.0000
6.500 0.8928 0.01143 0.00521 -0.0384 0.1497 1.0000
6.750 0.9142 0.01207 0.00566 -0.0376 0.1160 1.0000
7.000 0.9359 0.01269 0.00614 -0.0368 0.0940 1.0000
7.250 0.9583 0.01322 0.00662 -0.0361 0.0763 1.0000
7.500 0.9796 0.01386 0.00715 -0.0352 0.0583 1.0000
7.750 1.0003 0.01455 0.00778 -0.0342 0.0447 1.0000
8.000 1.0198 0.01536 0.00854 -0.0330 0.0362 1.0000
8.250 1.0420 0.01584 0.00908 -0.0322 0.0326 1.0000
8.500 1.0607 0.01665 0.00989 -0.0309 0.0290 1.0000
8.750 1.0791 0.01744 0.01076 -0.0296 0.0272 1.0000
9.000 1.0987 0.01808 0.01148 -0.0284 0.0256 1.0000
9.250 1.1171 0.01879 0.01223 -0.0272 0.0241 1.0000
9.500 1.1328 0.01968 0.01315 -0.0256 0.0226 1.0000
9.750 1.1414 0.02112 0.01470 -0.0230 0.0212 1.0000
10.000 1.1570 0.02184 0.01551 -0.0214 0.0206 1.0000
10.250 1.1695 0.02268 0.01644 -0.0192 0.0199 1.0000
10.500 1.1813 0.02355 0.01739 -0.0171 0.0191 1.0000
10.750 1.1923 0.02448 0.01839 -0.0150 0.0183 1.0000
11.000 1.2030 0.02540 0.01935 -0.0132 0.0175 1.0000
11.250 1.2093 0.02682 0.02083 -0.0109 0.0169 1.0000
11.500 1.2095 0.02922 0.02336 -0.0084 0.0161 1.0000
11.750 1.2191 0.03043 0.02471 -0.0068 0.0158 1.0000
12.000 1.2277 0.03173 0.02614 -0.0053 0.0154 1.0000
12.250 1.2345 0.03331 0.02785 -0.0038 0.0149 1.0000
12.500 1.2411 0.03482 0.02947 -0.0025 0.0144 1.0000
12.750 1.2457 0.03665 0.03142 -0.0013 0.0140 1.0000
13.000 1.2496 0.03851 0.03339 -0.0003 0.0136 1.0000
13.250 1.2530 0.04046 0.03543 0.0005 0.0132 1.0000
13.500 1.2555 0.04254 0.03758 0.0010 0.0128 1.0000
13.750 1.2539 0.04531 0.04043 0.0015 0.0125 1.0000
14.250 1.2331 0.05365 0.04917 0.0018 0.0119 1.0000
14.500 1.2294 0.05687 0.05255 0.0011 0.0118 1.0000
14.750 1.2211 0.06103 0.05689 0.0000 0.0117 1.0000
15.000 1.2116 0.06558 0.06163 -0.0016 0.0115 1.0000
15.250 1.2000 0.07080 0.06704 -0.0038 0.0114 1.0000
15.500 1.1877 0.07647 0.07289 -0.0066 0.0113 1.0000
15.750 1.1736 0.08289 0.07948 -0.0101 0.0112 1.0000
16.000 1.1558 0.09036 0.08714 -0.0143 0.0112 1.0000
16.250 1.1380 0.09827 0.09522 -0.0191 0.0112 1.0000
16.500 1.1148 0.10779 0.10491 -0.0249 0.0113 1.0000
16.750 1.0920 0.11776 0.11505 -0.0311 0.0114 1.0000
17.000 1.0677 0.12861 0.12606 -0.0380 0.0114 1.0000
17.250 1.0357 0.14191 0.13952 -0.0463 0.0117 1.0000
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