HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 2.0/9 AIRFOIL (hq209-il) Reynolds number: 500,000 Max Cl/Cd: 97.88 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq209-il-500000.txt Download as CSV file: xf-hq209-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.0/9 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4542 0.08328 0.08108 -0.0301 1.0000 0.0156
-8.500 -0.4561 0.07913 0.07696 -0.0322 1.0000 0.0157
-8.250 -0.4603 0.07483 0.07271 -0.0346 1.0000 0.0163
-8.000 -0.4692 0.07050 0.06843 -0.0371 1.0000 0.0163
-7.750 -0.4805 0.06463 0.06258 -0.0430 1.0000 0.0159
-7.500 -0.4869 0.05975 0.05765 -0.0455 1.0000 0.0163
-7.250 -0.4947 0.05579 0.05363 -0.0454 1.0000 0.0165
-7.000 -0.4980 0.05196 0.04971 -0.0452 0.9990 0.0167
-6.750 -0.4607 0.04689 0.04427 -0.0505 0.9950 0.0196
-6.500 -0.4349 0.04173 0.03873 -0.0547 0.9898 0.0198
-6.250 -0.4183 0.03093 0.02729 -0.0601 0.9842 0.0213
-6.000 -0.3867 0.02778 0.02393 -0.0628 0.9818 0.0222
-5.750 -0.3606 0.01883 0.01388 -0.0625 0.9756 0.0141
-5.500 -0.3269 0.01641 0.01108 -0.0638 0.9727 0.0136
-5.250 -0.2927 0.01465 0.00905 -0.0651 0.9701 0.0135
-5.000 -0.2628 0.01302 0.00726 -0.0656 0.9651 0.0138
-4.750 -0.2328 0.01189 0.00603 -0.0661 0.9594 0.0148
-4.500 -0.2007 0.01118 0.00525 -0.0670 0.9552 0.0167
-4.250 -0.1739 0.01062 0.00461 -0.0667 0.9471 0.0187
-4.000 -0.1451 0.00994 0.00387 -0.0669 0.9413 0.0237
-3.750 -0.1193 0.00940 0.00331 -0.0664 0.9327 0.0377
-3.500 -0.0918 0.00906 0.00296 -0.0662 0.9262 0.0566
-3.250 -0.0657 0.00874 0.00270 -0.0659 0.9179 0.0808
-3.000 -0.0401 0.00820 0.00244 -0.0656 0.9107 0.1550
-2.750 -0.0163 0.00734 0.00218 -0.0653 0.9025 0.3252
-2.500 0.0073 0.00665 0.00206 -0.0648 0.8945 0.5110
-2.250 0.0331 0.00645 0.00201 -0.0642 0.8869 0.5822
-2.000 0.0594 0.00637 0.00197 -0.0637 0.8781 0.6216
-1.750 0.0862 0.00633 0.00192 -0.0633 0.8705 0.6498
-1.500 0.1127 0.00629 0.00189 -0.0628 0.8618 0.6778
-1.250 0.1391 0.00626 0.00188 -0.0623 0.8528 0.7023
-1.000 0.1656 0.00624 0.00184 -0.0617 0.8434 0.7230
-0.750 0.1918 0.00622 0.00183 -0.0611 0.8330 0.7461
-0.500 0.2183 0.00620 0.00182 -0.0606 0.8233 0.7642
-0.250 0.2447 0.00618 0.00180 -0.0601 0.8140 0.7820
0.000 0.2711 0.00616 0.00178 -0.0595 0.8039 0.7985
0.250 0.2978 0.00612 0.00175 -0.0591 0.7926 0.8104
0.500 0.3247 0.00610 0.00173 -0.0588 0.7819 0.8219
0.750 0.3515 0.00608 0.00170 -0.0584 0.7716 0.8343
1.000 0.3780 0.00606 0.00169 -0.0580 0.7611 0.8479
1.250 0.4042 0.00602 0.00169 -0.0575 0.7497 0.8634
1.500 0.4299 0.00598 0.00169 -0.0569 0.7373 0.8829
1.750 0.4554 0.00592 0.00170 -0.0561 0.7246 0.9097
2.000 0.4885 0.00589 0.00170 -0.0570 0.7104 0.9538
2.250 0.5278 0.00593 0.00172 -0.0596 0.6938 1.0000
2.500 0.5547 0.00603 0.00176 -0.0594 0.6763 1.0000
2.750 0.5813 0.00615 0.00182 -0.0592 0.6561 1.0000
3.000 0.6076 0.00629 0.00189 -0.0589 0.6327 1.0000
3.250 0.6333 0.00647 0.00197 -0.0584 0.6011 1.0000
3.500 0.6574 0.00678 0.00209 -0.0577 0.5511 1.0000
3.750 0.6801 0.00724 0.00225 -0.0568 0.4818 1.0000
4.000 0.7037 0.00769 0.00246 -0.0562 0.4256 1.0000
4.250 0.7274 0.00816 0.00271 -0.0556 0.3735 1.0000
4.500 0.7511 0.00864 0.00300 -0.0550 0.3225 1.0000
4.750 0.7747 0.00914 0.00330 -0.0545 0.2800 1.0000
5.000 0.7990 0.00958 0.00359 -0.0540 0.2480 1.0000
5.250 0.8238 0.00996 0.00388 -0.0536 0.2227 1.0000
5.500 0.8486 0.01033 0.00417 -0.0533 0.1963 1.0000
5.750 0.8722 0.01084 0.00453 -0.0527 0.1533 1.0000
6.000 0.8928 0.01171 0.00504 -0.0519 0.0922 1.0000
6.250 0.9149 0.01241 0.00556 -0.0511 0.0622 1.0000
6.500 0.9385 0.01293 0.00603 -0.0506 0.0503 1.0000
6.750 0.9621 0.01342 0.00651 -0.0500 0.0425 1.0000
7.000 0.9865 0.01381 0.00694 -0.0495 0.0372 1.0000
7.250 1.0099 0.01430 0.00742 -0.0489 0.0311 1.0000
7.500 1.0341 0.01468 0.00785 -0.0485 0.0242 1.0000
7.750 1.0545 0.01557 0.00866 -0.0474 0.0126 1.0000
8.000 1.0764 0.01624 0.00939 -0.0465 0.0098 1.0000
8.250 1.0954 0.01727 0.01051 -0.0452 0.0079 1.0000
8.500 1.1160 0.01803 0.01137 -0.0441 0.0074 1.0000
8.750 1.1352 0.01893 0.01239 -0.0429 0.0070 1.0000
9.000 1.1530 0.01994 0.01353 -0.0414 0.0067 1.0000
9.250 1.1704 0.02096 0.01466 -0.0400 0.0062 1.0000
9.500 1.1860 0.02211 0.01597 -0.0384 0.0060 1.0000
9.750 1.2001 0.02337 0.01735 -0.0366 0.0056 1.0000
10.000 1.2122 0.02482 0.01894 -0.0346 0.0055 1.0000
10.250 1.2210 0.02656 0.02086 -0.0322 0.0053 1.0000
10.500 1.2251 0.02854 0.02303 -0.0292 0.0051 1.0000
10.750 1.2270 0.03062 0.02532 -0.0260 0.0051 1.0000
11.000 1.2275 0.03281 0.02774 -0.0230 0.0050 1.0000
11.250 1.2280 0.03492 0.03005 -0.0204 0.0051 1.0000
11.500 1.2256 0.03735 0.03269 -0.0179 0.0051 1.0000
11.750 1.2196 0.04022 0.03580 -0.0157 0.0051 1.0000
12.000 1.2105 0.04349 0.03930 -0.0139 0.0051 1.0000
12.250 1.2024 0.04679 0.04283 -0.0128 0.0052 1.0000
12.500 1.1904 0.05078 0.04705 -0.0124 0.0052 1.0000
12.750 1.1747 0.05566 0.05220 -0.0129 0.0054 1.0000
13.000 1.1554 0.06146 0.05823 -0.0145 0.0054 1.0000
13.250 1.1328 0.06854 0.06557 -0.0176 0.0055 1.0000
13.500 1.1093 0.07664 0.07390 -0.0222 0.0056 1.0000
13.750 1.0858 0.08583 0.08328 -0.0281 0.0057 1.0000
14.000 1.0631 0.09594 0.09356 -0.0348 0.0057 1.0000
14.250 1.0396 0.10730 0.10508 -0.0421 0.0058 1.0000
14.500 1.0127 0.12032 0.11823 -0.0501 0.0059 1.0000
14.750 0.8719 0.12861 0.12678 -0.0530 0.0059 1.0000
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Polar data table (+)
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