HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 0/10 AIRFOIL (hq010-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.96 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq010-il-1000000.txt Download as CSV file: xf-hq010-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 0/10 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9114 0.11132 0.10949 0.0107 1.0000 0.0030
-15.000 -0.9436 0.09926 0.09735 0.0043 1.0000 0.0030
-14.750 -0.9884 0.08458 0.08254 -0.0040 1.0000 0.0030
-14.500 -1.0166 0.07336 0.07118 -0.0110 1.0000 0.0029
-14.250 -1.0364 0.06465 0.06233 -0.0170 1.0000 0.0029
-14.000 -1.0606 0.05616 0.05366 -0.0227 1.0000 0.0029
-13.750 -1.0807 0.04962 0.04694 -0.0265 1.0000 0.0029
-13.500 -1.0946 0.04475 0.04190 -0.0286 1.0000 0.0029
-13.250 -1.1098 0.04030 0.03728 -0.0297 1.0000 0.0029
-13.000 -1.1245 0.03645 0.03322 -0.0297 1.0000 0.0029
-12.750 -1.1339 0.03355 0.03014 -0.0287 1.0000 0.0029
-12.500 -1.1413 0.03116 0.02757 -0.0268 1.0000 0.0029
-12.250 -1.1470 0.02916 0.02541 -0.0241 1.0000 0.0029
-12.000 -1.1518 0.02741 0.02348 -0.0206 1.0000 0.0029
-11.750 -1.1499 0.02567 0.02155 -0.0178 1.0000 0.0029
-11.500 -1.1408 0.02421 0.01991 -0.0159 1.0000 0.0029
-11.250 -1.1293 0.02283 0.01836 -0.0142 1.0000 0.0029
-11.000 -1.1164 0.02145 0.01680 -0.0125 1.0000 0.0029
-10.750 -1.1007 0.02029 0.01550 -0.0112 1.0000 0.0029
-10.500 -1.0836 0.01920 0.01427 -0.0099 1.0000 0.0029
-10.250 -1.0652 0.01822 0.01316 -0.0088 1.0000 0.0030
-10.000 -1.0457 0.01731 0.01213 -0.0078 1.0000 0.0030
-9.750 -1.0253 0.01648 0.01119 -0.0069 1.0000 0.0031
-9.500 -1.0038 0.01577 0.01038 -0.0061 1.0000 0.0031
-9.250 -0.9823 0.01499 0.00950 -0.0052 1.0000 0.0033
-9.000 -0.9608 0.01420 0.00857 -0.0044 1.0000 0.0037
-8.750 -0.9380 0.01358 0.00791 -0.0037 1.0000 0.0044
-8.500 -0.9156 0.01293 0.00730 -0.0030 1.0000 0.0076
-8.250 -0.8910 0.01259 0.00702 -0.0026 1.0000 0.0115
-8.000 -0.8655 0.01239 0.00682 -0.0023 1.0000 0.0130
-7.750 -0.8392 0.01230 0.00674 -0.0022 1.0000 0.0137
-7.500 -0.8151 0.01189 0.00629 -0.0017 1.0000 0.0148
-7.250 -0.7914 0.01141 0.00576 -0.0010 1.0000 0.0165
-7.000 -0.7668 0.01110 0.00545 -0.0006 1.0000 0.0179
-6.750 -0.7421 0.01082 0.00517 -0.0001 1.0000 0.0192
-6.500 -0.7175 0.01058 0.00491 0.0004 1.0000 0.0204
-6.250 -0.6925 0.01045 0.00479 0.0009 1.0000 0.0212
-6.000 -0.6677 0.00992 0.00424 0.0013 0.9984 0.0257
-5.750 -0.6323 0.00961 0.00394 -0.0006 0.9890 0.0295
-5.500 -0.5959 0.00924 0.00355 -0.0026 0.9785 0.0361
-5.250 -0.5598 0.00889 0.00324 -0.0046 0.9655 0.0470
-5.000 -0.5290 0.00858 0.00298 -0.0053 0.9447 0.0622
-4.750 -0.5035 0.00835 0.00276 -0.0048 0.9200 0.0786
-4.500 -0.4793 0.00811 0.00253 -0.0041 0.8976 0.0996
-4.250 -0.4555 0.00771 0.00225 -0.0034 0.8794 0.1430
-4.000 -0.4308 0.00738 0.00207 -0.0029 0.8642 0.1977
-3.750 -0.4048 0.00720 0.00192 -0.0026 0.8499 0.2211
-3.500 -0.3790 0.00697 0.00176 -0.0022 0.8363 0.2535
-3.250 -0.3532 0.00669 0.00158 -0.0019 0.8241 0.2958
-3.000 -0.3287 0.00621 0.00140 -0.0015 0.8135 0.3846
-2.750 -0.3024 0.00594 0.00128 -0.0013 0.8038 0.4388
-2.500 -0.2763 0.00566 0.00117 -0.0010 0.7949 0.4920
-2.250 -0.2501 0.00544 0.00109 -0.0007 0.7860 0.5457
-2.000 -0.2232 0.00529 0.00104 -0.0005 0.7769 0.5901
-1.750 -0.1957 0.00521 0.00101 -0.0004 0.7690 0.6167
-1.500 -0.1680 0.00517 0.00099 -0.0003 0.7613 0.6363
-1.250 -0.1403 0.00513 0.00098 -0.0002 0.7536 0.6591
-0.750 -0.0843 0.00511 0.00094 -0.0001 0.7353 0.6806
-0.500 -0.0561 0.00512 0.00092 -0.0001 0.7254 0.6901
-0.250 -0.0282 0.00512 0.00091 0.0000 0.7160 0.6988
0.000 0.0000 0.00511 0.00091 0.0000 0.7073 0.7073
0.250 0.0282 0.00512 0.00091 0.0000 0.6988 0.7161
0.500 0.0562 0.00512 0.00092 0.0001 0.6901 0.7253
0.750 0.0843 0.00511 0.00094 0.0001 0.6806 0.7353
1.250 0.1403 0.00513 0.00098 0.0002 0.6590 0.7537
1.500 0.1680 0.00517 0.00099 0.0003 0.6362 0.7613
1.750 0.1957 0.00521 0.00101 0.0004 0.6166 0.7690
2.000 0.2232 0.00528 0.00104 0.0005 0.5903 0.7769
2.250 0.2501 0.00544 0.00109 0.0007 0.5463 0.7860
2.500 0.2763 0.00566 0.00117 0.0010 0.4917 0.7948
2.750 0.3025 0.00594 0.00128 0.0013 0.4386 0.8038
3.000 0.3287 0.00621 0.00140 0.0015 0.3841 0.8136
3.250 0.3532 0.00669 0.00158 0.0019 0.2958 0.8240
3.500 0.3790 0.00697 0.00176 0.0022 0.2534 0.8364
3.750 0.4049 0.00720 0.00192 0.0026 0.2213 0.8499
4.000 0.4309 0.00737 0.00207 0.0029 0.1980 0.8643
4.250 0.4554 0.00772 0.00225 0.0034 0.1413 0.8794
4.500 0.4794 0.00811 0.00253 0.0041 0.0996 0.8976
4.750 0.5035 0.00835 0.00276 0.0048 0.0785 0.9199
5.000 0.5290 0.00858 0.00298 0.0053 0.0622 0.9447
5.250 0.5598 0.00889 0.00324 0.0046 0.0467 0.9655
5.500 0.5958 0.00924 0.00355 0.0026 0.0363 0.9786
5.750 0.6323 0.00961 0.00394 0.0006 0.0295 0.9891
6.000 0.6676 0.00993 0.00423 -0.0013 0.0251 0.9984
6.250 0.6927 0.01042 0.00475 -0.0009 0.0212 1.0000
6.500 0.7175 0.01057 0.00489 -0.0004 0.0203 1.0000
6.750 0.7422 0.01081 0.00515 0.0001 0.0192 1.0000
7.000 0.7669 0.01108 0.00543 0.0006 0.0177 1.0000
7.250 0.7913 0.01142 0.00576 0.0010 0.0164 1.0000
7.500 0.8150 0.01190 0.00629 0.0017 0.0146 1.0000
7.750 0.8394 0.01228 0.00671 0.0022 0.0137 1.0000
8.000 0.8653 0.01241 0.00685 0.0024 0.0130 1.0000
8.250 0.8912 0.01256 0.00697 0.0026 0.0112 1.0000
8.500 0.9155 0.01293 0.00730 0.0030 0.0076 1.0000
8.750 0.9380 0.01358 0.00790 0.0037 0.0044 1.0000
9.000 0.9607 0.01420 0.00857 0.0044 0.0037 1.0000
9.500 1.0038 0.01574 0.01035 0.0061 0.0032 1.0000
9.750 1.0251 0.01648 0.01119 0.0069 0.0031 1.0000
10.000 1.0456 0.01730 0.01212 0.0078 0.0030 1.0000
10.250 1.0650 0.01821 0.01315 0.0089 0.0030 1.0000
10.500 1.0835 0.01919 0.01425 0.0100 0.0030 1.0000
10.750 1.1008 0.02025 0.01545 0.0112 0.0029 1.0000
11.000 1.1162 0.02144 0.01680 0.0126 0.0029 1.0000
11.250 1.1299 0.02273 0.01824 0.0141 0.0029 1.0000
11.500 1.1402 0.02425 0.01995 0.0160 0.0029 1.0000
11.750 1.1489 0.02574 0.02162 0.0179 0.0029 1.0000
12.000 1.1503 0.02749 0.02357 0.0208 0.0029 1.0000
12.250 1.1472 0.02912 0.02536 0.0241 0.0029 1.0000
12.500 1.1417 0.03110 0.02751 0.0268 0.0029 1.0000
12.750 1.1347 0.03346 0.03005 0.0287 0.0029 1.0000
13.000 1.1203 0.03686 0.03366 0.0298 0.0029 1.0000
13.250 1.1137 0.03985 0.03680 0.0298 0.0029 1.0000
13.500 1.0967 0.04448 0.04162 0.0287 0.0029 1.0000
13.750 1.0802 0.04969 0.04702 0.0265 0.0029 1.0000
14.000 1.0647 0.05551 0.05299 0.0231 0.0029 1.0000
14.250 1.0355 0.06488 0.06257 0.0168 0.0029 1.0000
14.500 1.0153 0.07375 0.07158 0.0107 0.0029 1.0000
14.750 0.9860 0.08523 0.08321 0.0035 0.0030 1.0000
15.000 0.9528 0.09728 0.09537 -0.0033 0.0030 1.0000
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