HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 200,000 Max Cl/Cd: 68.34 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2090sm-il-200000-n5.txt Download as CSV file: xf-hq2090sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ-2.0/9 9.0% smoothed
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4714 0.08829 0.08475 -0.0276 1.0000 0.0123
-9.000 -0.4765 0.08284 0.07935 -0.0305 1.0000 0.0119
-8.750 -0.4861 0.07628 0.07287 -0.0343 1.0000 0.0115
-8.500 -0.5024 0.06737 0.06409 -0.0409 1.0000 0.0108
-8.250 -0.5120 0.06063 0.05731 -0.0465 1.0000 0.0106
-8.000 -0.5203 0.05539 0.05196 -0.0488 1.0000 0.0105
-7.750 -0.5275 0.05036 0.04680 -0.0495 1.0000 0.0104
-7.500 -0.5330 0.04536 0.04159 -0.0492 1.0000 0.0103
-7.250 -0.5367 0.04046 0.03640 -0.0480 1.0000 0.0103
-7.000 -0.5312 0.03521 0.03069 -0.0478 0.9983 0.0103
-6.750 -0.5060 0.02942 0.02416 -0.0507 0.9922 0.0103
-6.500 -0.4769 0.02532 0.01937 -0.0527 0.9873 0.0106
-6.250 -0.4485 0.02213 0.01566 -0.0540 0.9823 0.0111
-6.000 -0.4164 0.02050 0.01379 -0.0556 0.9783 0.0120
-5.750 -0.3841 0.01950 0.01260 -0.0569 0.9741 0.0136
-5.500 -0.3520 0.01828 0.01113 -0.0580 0.9695 0.0157
-5.250 -0.3197 0.01658 0.00925 -0.0592 0.9660 0.0173
-5.000 -0.2900 0.01573 0.00833 -0.0598 0.9598 0.0197
-4.750 -0.2571 0.01512 0.00758 -0.0609 0.9551 0.0242
-4.500 -0.2269 0.01426 0.00667 -0.0618 0.9495 0.0313
-4.250 -0.1965 0.01368 0.00601 -0.0624 0.9431 0.0391
-4.000 -0.1640 0.01324 0.00550 -0.0635 0.9385 0.0483
-3.750 -0.1363 0.01272 0.00496 -0.0636 0.9304 0.0564
-3.500 -0.1050 0.01228 0.00447 -0.0644 0.9252 0.0688
-3.250 -0.0779 0.01187 0.00411 -0.0644 0.9168 0.0920
-2.750 -0.0224 0.01078 0.00347 -0.0650 0.9024 0.2302
-2.500 0.0026 0.00979 0.00328 -0.0650 0.8957 0.4438
-2.250 0.0274 0.00942 0.00326 -0.0643 0.8875 0.5567
-2.000 0.0542 0.00928 0.00324 -0.0638 0.8805 0.6173
-1.750 0.0808 0.00922 0.00320 -0.0632 0.8725 0.6583
-1.500 0.1071 0.00917 0.00318 -0.0625 0.8645 0.6946
-1.250 0.1326 0.00911 0.00316 -0.0616 0.8562 0.7319
-1.000 0.1575 0.00906 0.00314 -0.0606 0.8465 0.7604
-0.750 0.1844 0.00902 0.00306 -0.0601 0.8380 0.7740
-0.500 0.2113 0.00899 0.00299 -0.0597 0.8293 0.7854
0.000 0.2650 0.00894 0.00288 -0.0588 0.8128 0.8084
0.250 0.2911 0.00891 0.00286 -0.0583 0.8024 0.8204
0.500 0.3172 0.00887 0.00282 -0.0576 0.7900 0.8333
0.750 0.3431 0.00883 0.00276 -0.0569 0.7761 0.8477
1.000 0.3692 0.00880 0.00274 -0.0563 0.7634 0.8640
1.250 0.3959 0.00878 0.00274 -0.0558 0.7524 0.8835
1.500 0.4243 0.00875 0.00273 -0.0556 0.7406 0.9077
1.750 0.4573 0.00873 0.00272 -0.0565 0.7266 0.9391
2.000 0.4949 0.00873 0.00272 -0.0586 0.7092 0.9996
2.250 0.5215 0.00882 0.00277 -0.0583 0.6917 1.0000
2.500 0.5481 0.00893 0.00282 -0.0580 0.6732 1.0000
2.750 0.5745 0.00905 0.00290 -0.0577 0.6527 1.0000
3.000 0.6006 0.00919 0.00301 -0.0573 0.6290 1.0000
3.250 0.6263 0.00937 0.00311 -0.0568 0.6003 1.0000
3.500 0.6516 0.00959 0.00323 -0.0563 0.5659 1.0000
3.750 0.6759 0.00989 0.00338 -0.0556 0.5247 1.0000
4.000 0.6985 0.01034 0.00361 -0.0546 0.4685 1.0000
4.250 0.7201 0.01093 0.00389 -0.0536 0.4058 1.0000
4.500 0.7427 0.01148 0.00422 -0.0529 0.3534 1.0000
4.750 0.7654 0.01204 0.00459 -0.0522 0.3068 1.0000
5.000 0.7879 0.01264 0.00499 -0.0515 0.2632 1.0000
5.250 0.8111 0.01318 0.00544 -0.0510 0.2274 1.0000
5.500 0.8344 0.01372 0.00588 -0.0504 0.1945 1.0000
5.750 0.8575 0.01429 0.00635 -0.0498 0.1637 1.0000
6.000 0.8801 0.01493 0.00687 -0.0492 0.1301 1.0000
6.250 0.9018 0.01567 0.00747 -0.0485 0.0979 1.0000
6.500 0.9240 0.01638 0.00812 -0.0478 0.0779 1.0000
6.750 0.9460 0.01710 0.00888 -0.0470 0.0653 1.0000
7.000 0.9677 0.01783 0.00960 -0.0463 0.0532 1.0000
7.250 0.9896 0.01850 0.01027 -0.0456 0.0419 1.0000
7.500 1.0106 0.01930 0.01110 -0.0448 0.0349 1.0000
7.750 1.0321 0.02001 0.01190 -0.0440 0.0277 1.0000
8.000 1.0520 0.02091 0.01286 -0.0429 0.0205 1.0000
8.250 1.0699 0.02206 0.01404 -0.0417 0.0163 1.0000
8.500 1.0879 0.02315 0.01533 -0.0404 0.0141 1.0000
8.750 1.1050 0.02430 0.01660 -0.0390 0.0126 1.0000
9.000 1.1194 0.02571 0.01810 -0.0374 0.0114 1.0000
9.250 1.1343 0.02705 0.01960 -0.0359 0.0104 1.0000
9.500 1.1490 0.02836 0.02109 -0.0343 0.0094 1.0000
9.750 1.1615 0.02992 0.02284 -0.0326 0.0089 1.0000
10.000 1.1721 0.03158 0.02468 -0.0306 0.0084 1.0000
10.250 1.1801 0.03329 0.02657 -0.0284 0.0081 1.0000
10.500 1.1860 0.03510 0.02857 -0.0261 0.0077 1.0000
10.750 1.1897 0.03713 0.03081 -0.0238 0.0075 1.0000
11.000 1.1909 0.03937 0.03326 -0.0217 0.0073 1.0000
11.250 1.1886 0.04204 0.03616 -0.0196 0.0071 1.0000
11.500 1.1845 0.04498 0.03940 -0.0179 0.0070 1.0000
11.750 1.1776 0.04827 0.04294 -0.0166 0.0070 1.0000
12.000 1.1661 0.05225 0.04718 -0.0159 0.0069 1.0000
12.250 1.1533 0.05664 0.05182 -0.0159 0.0068 1.0000
12.500 1.1406 0.06127 0.05669 -0.0168 0.0068 1.0000
12.750 1.1262 0.06654 0.06219 -0.0186 0.0068 1.0000
13.000 1.1085 0.07289 0.06876 -0.0215 0.0068 1.0000
13.250 1.0925 0.07958 0.07566 -0.0253 0.0068 1.0000
13.500 1.0757 0.08723 0.08350 -0.0302 0.0068 1.0000
13.750 1.0585 0.09579 0.09224 -0.0358 0.0069 1.0000
14.000 1.0382 0.10593 0.10252 -0.0424 0.0070 1.0000
14.250 1.0055 0.12081 0.11761 -0.0517 0.0073 1.0000
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Polar data table (+)
Polar graphs
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