HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il) Reynolds number: 500,000 Max Cl/Cd: 97.22 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq2090sm-il-500000.txt Download as CSV file: xf-hq2090sm-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3825 0.10125 0.09908 -0.0219 1.0000 0.0187
-10.250 -0.3840 0.09639 0.09424 -0.0244 1.0000 0.0196
-6.500 -0.4695 0.02626 0.02209 -0.0541 0.9883 0.0142
-6.250 -0.4408 0.02075 0.01603 -0.0561 0.9850 0.0131
-6.000 -0.4071 0.01761 0.01241 -0.0579 0.9830 0.0132
-5.750 -0.3758 0.01596 0.01047 -0.0587 0.9786 0.0137
-5.500 -0.3436 0.01379 0.00803 -0.0599 0.9753 0.0147
-5.250 -0.3088 0.01272 0.00689 -0.0617 0.9726 0.0163
-5.000 -0.2727 0.01225 0.00638 -0.0635 0.9701 0.0187
-4.750 -0.2432 0.01130 0.00533 -0.0640 0.9639 0.0219
-4.500 -0.2111 0.01072 0.00472 -0.0649 0.9588 0.0267
-4.250 -0.1812 0.01013 0.00409 -0.0654 0.9528 0.0339
-4.000 -0.1525 0.00997 0.00389 -0.0655 0.9454 0.0400
-3.750 -0.1254 0.00947 0.00339 -0.0653 0.9380 0.0500
-3.500 -0.0989 0.00912 0.00301 -0.0650 0.9299 0.0619
-3.250 -0.0728 0.00875 0.00270 -0.0646 0.9215 0.0845
-3.000 -0.0469 0.00826 0.00242 -0.0643 0.9139 0.1470
-2.750 -0.0232 0.00740 0.00215 -0.0640 0.9044 0.3094
-2.500 0.0007 0.00669 0.00198 -0.0635 0.8959 0.4892
-2.250 0.0260 0.00641 0.00192 -0.0629 0.8867 0.5722
-2.000 0.0519 0.00628 0.00190 -0.0623 0.8770 0.6252
-1.750 0.0787 0.00625 0.00186 -0.0618 0.8687 0.6585
-1.500 0.1055 0.00622 0.00184 -0.0614 0.8603 0.6843
-1.250 0.1326 0.00622 0.00182 -0.0611 0.8522 0.7036
-1.000 0.1595 0.00621 0.00181 -0.0606 0.8443 0.7226
-0.750 0.1862 0.00621 0.00180 -0.0602 0.8347 0.7441
-0.500 0.2120 0.00619 0.00181 -0.0594 0.8244 0.7674
-0.250 0.2383 0.00619 0.00179 -0.0588 0.8138 0.7847
0.000 0.2653 0.00616 0.00176 -0.0585 0.8035 0.7947
0.250 0.2925 0.00614 0.00175 -0.0582 0.7944 0.8050
0.500 0.3196 0.00614 0.00173 -0.0579 0.7855 0.8160
0.750 0.3465 0.00613 0.00172 -0.0576 0.7749 0.8276
1.000 0.3731 0.00610 0.00172 -0.0572 0.7634 0.8399
1.250 0.3995 0.00608 0.00173 -0.0567 0.7518 0.8537
1.500 0.4256 0.00606 0.00174 -0.0562 0.7404 0.8703
1.750 0.4509 0.00603 0.00175 -0.0554 0.7284 0.8908
2.000 0.4763 0.00599 0.00176 -0.0546 0.7156 0.9211
2.250 0.5114 0.00596 0.00178 -0.0560 0.7008 0.9639
2.500 0.5469 0.00601 0.00180 -0.0578 0.6834 1.0000
2.750 0.5739 0.00611 0.00185 -0.0576 0.6641 1.0000
3.000 0.6006 0.00624 0.00192 -0.0574 0.6402 1.0000
3.250 0.6261 0.00644 0.00199 -0.0569 0.6029 1.0000
3.500 0.6508 0.00672 0.00209 -0.0563 0.5546 1.0000
3.750 0.6749 0.00710 0.00224 -0.0557 0.5003 1.0000
4.000 0.6985 0.00756 0.00247 -0.0550 0.4419 1.0000
4.250 0.7224 0.00804 0.00271 -0.0545 0.3878 1.0000
4.500 0.7461 0.00854 0.00298 -0.0539 0.3333 1.0000
4.750 0.7703 0.00900 0.00327 -0.0535 0.2898 1.0000
5.000 0.7948 0.00944 0.00357 -0.0531 0.2551 1.0000
5.250 0.8194 0.00988 0.00389 -0.0526 0.2213 1.0000
5.500 0.8434 0.01037 0.00423 -0.0522 0.1836 1.0000
5.750 0.8668 0.01095 0.00461 -0.0517 0.1428 1.0000
6.000 0.8888 0.01169 0.00508 -0.0510 0.0939 1.0000
6.250 0.9113 0.01238 0.00562 -0.0503 0.0664 1.0000
6.500 0.9345 0.01297 0.00616 -0.0497 0.0526 1.0000
6.750 0.9586 0.01344 0.00664 -0.0492 0.0438 1.0000
7.000 0.9823 0.01394 0.00715 -0.0486 0.0354 1.0000
7.250 1.0048 0.01460 0.00781 -0.0478 0.0263 1.0000
7.500 1.0254 0.01553 0.00875 -0.0467 0.0192 1.0000
7.750 1.0474 0.01622 0.00949 -0.0459 0.0160 1.0000
8.000 1.0653 0.01743 0.01080 -0.0444 0.0137 1.0000
8.250 1.0868 0.01812 0.01158 -0.0435 0.0124 1.0000
8.500 1.1068 0.01898 0.01252 -0.0424 0.0115 1.0000
8.750 1.1257 0.01994 0.01355 -0.0412 0.0107 1.0000
9.000 1.1405 0.02143 0.01515 -0.0395 0.0100 1.0000
9.250 1.1493 0.02411 0.01804 -0.0369 0.0095 1.0000
9.500 1.1667 0.02534 0.01944 -0.0356 0.0093 1.0000
9.750 1.1822 0.02688 0.02119 -0.0340 0.0090 1.0000
10.000 1.1952 0.02883 0.02335 -0.0322 0.0088 1.0000
10.250 1.2058 0.03104 0.02580 -0.0302 0.0087 1.0000
10.500 1.2143 0.03315 0.02815 -0.0280 0.0084 1.0000
10.750 1.2180 0.03519 0.03042 -0.0253 0.0082 1.0000
11.000 1.2164 0.03748 0.03294 -0.0221 0.0081 1.0000
11.250 1.2187 0.03879 0.03437 -0.0197 0.0077 1.0000
11.500 1.2120 0.04150 0.03731 -0.0170 0.0076 1.0000
11.750 1.2008 0.04478 0.04085 -0.0147 0.0076 1.0000
12.000 1.1840 0.04892 0.04527 -0.0131 0.0077 1.0000
12.250 1.1719 0.05262 0.04916 -0.0126 0.0076 1.0000
12.500 1.1551 0.05731 0.05406 -0.0130 0.0077 1.0000
12.750 1.1267 0.06435 0.06139 -0.0151 0.0079 1.0000
13.000 1.1063 0.07092 0.06814 -0.0183 0.0079 1.0000
13.250 1.0842 0.07876 0.07617 -0.0231 0.0080 1.0000
13.500 1.0644 0.08720 0.08477 -0.0288 0.0080 1.0000
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Polar data table (+)
Polar graphs
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