HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il) Reynolds number: 200,000 Max Cl/Cd: 70.57 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq2512-il-200000-n5.txt Download as CSV file: xf-hq2512-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 2.5/12 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4650 0.08870 0.08516 -0.0450 1.0000 0.0138
-10.750 -0.4860 0.08001 0.07653 -0.0492 1.0000 0.0137
-10.250 -0.5735 0.05314 0.04955 -0.0673 1.0000 0.0128
-10.000 -0.6087 0.04811 0.04441 -0.0682 1.0000 0.0121
-9.750 -0.6380 0.04561 0.04183 -0.0648 1.0000 0.0121
-9.500 -0.6541 0.04074 0.03659 -0.0651 0.9944 0.0123
-9.250 -0.6439 0.03515 0.03036 -0.0688 0.9847 0.0129
-9.000 -0.6275 0.03093 0.02555 -0.0706 0.9765 0.0133
-8.750 -0.6025 0.02778 0.02189 -0.0726 0.9716 0.0138
-8.500 -0.5795 0.02543 0.01920 -0.0733 0.9644 0.0144
-8.250 -0.5510 0.02397 0.01758 -0.0747 0.9592 0.0153
-8.000 -0.5230 0.02282 0.01628 -0.0756 0.9533 0.0162
-7.750 -0.4945 0.02190 0.01516 -0.0764 0.9470 0.0180
-7.500 -0.4641 0.02065 0.01367 -0.0775 0.9425 0.0196
-7.250 -0.4394 0.01965 0.01262 -0.0775 0.9344 0.0212
-7.000 -0.4095 0.01881 0.01166 -0.0783 0.9293 0.0234
-6.750 -0.3835 0.01801 0.01070 -0.0782 0.9218 0.0262
-6.500 -0.3554 0.01726 0.00992 -0.0787 0.9160 0.0301
-6.250 -0.3279 0.01684 0.00937 -0.0788 0.9092 0.0351
-6.000 -0.3012 0.01619 0.00867 -0.0789 0.9029 0.0395
-5.750 -0.2736 0.01585 0.00825 -0.0790 0.8965 0.0451
-5.500 -0.2478 0.01535 0.00771 -0.0788 0.8895 0.0505
-5.250 -0.2209 0.01496 0.00725 -0.0787 0.8834 0.0559
-5.000 -0.1951 0.01459 0.00676 -0.0784 0.8762 0.0606
-4.750 -0.1688 0.01408 0.00624 -0.0783 0.8705 0.0668
-4.500 -0.1431 0.01377 0.00585 -0.0779 0.8631 0.0740
-4.250 -0.1165 0.01335 0.00542 -0.0778 0.8575 0.0838
-4.000 -0.0909 0.01301 0.00507 -0.0775 0.8503 0.0975
-3.750 -0.0646 0.01263 0.00473 -0.0773 0.8444 0.1213
-3.500 -0.0392 0.01219 0.00446 -0.0771 0.8379 0.1695
-3.250 -0.0142 0.01166 0.00419 -0.0769 0.8314 0.2463
-3.000 0.0095 0.01097 0.00396 -0.0766 0.8253 0.3701
-2.750 0.0334 0.01056 0.00393 -0.0759 0.8184 0.4810
-2.500 0.0598 0.01042 0.00391 -0.0755 0.8130 0.5408
-2.250 0.0859 0.01038 0.00392 -0.0750 0.8058 0.5788
-2.000 0.1131 0.01036 0.00388 -0.0746 0.8000 0.6099
-1.750 0.1392 0.01038 0.00393 -0.0740 0.7929 0.6401
-1.500 0.1659 0.01040 0.00394 -0.0735 0.7865 0.6645
-1.250 0.1927 0.01041 0.00392 -0.0731 0.7794 0.6797
-1.000 0.2199 0.01041 0.00389 -0.0727 0.7727 0.6928
-0.750 0.2467 0.01043 0.00389 -0.0723 0.7656 0.7059
-0.500 0.2738 0.01044 0.00386 -0.0720 0.7589 0.7173
-0.250 0.3014 0.01045 0.00383 -0.0719 0.7523 0.7267
0.000 0.3285 0.01044 0.00381 -0.0716 0.7447 0.7334
0.250 0.3558 0.01045 0.00377 -0.0714 0.7358 0.7414
0.500 0.3828 0.01043 0.00371 -0.0710 0.7261 0.7483
0.750 0.4096 0.01043 0.00367 -0.0706 0.7143 0.7564
1.000 0.4359 0.01042 0.00367 -0.0702 0.7027 0.7638
1.250 0.4628 0.01044 0.00366 -0.0699 0.6924 0.7720
1.500 0.4896 0.01046 0.00366 -0.0695 0.6833 0.7801
1.750 0.5160 0.01048 0.00370 -0.0691 0.6728 0.7884
2.000 0.5425 0.01051 0.00374 -0.0688 0.6624 0.7976
2.250 0.5686 0.01053 0.00378 -0.0683 0.6511 0.8063
2.500 0.5948 0.01056 0.00381 -0.0679 0.6389 0.8161
2.750 0.6206 0.01061 0.00387 -0.0674 0.6252 0.8267
3.000 0.6458 0.01064 0.00393 -0.0667 0.6105 0.8380
3.250 0.6709 0.01069 0.00400 -0.0660 0.5940 0.8508
3.500 0.6959 0.01074 0.00407 -0.0654 0.5757 0.8660
4.000 0.7481 0.01092 0.00426 -0.0645 0.5293 0.9133
4.250 0.7840 0.01111 0.00437 -0.0663 0.4959 0.9995
4.500 0.8070 0.01144 0.00457 -0.0656 0.4636 1.0000
4.750 0.8293 0.01183 0.00480 -0.0647 0.4314 1.0000
5.000 0.8512 0.01225 0.00508 -0.0638 0.4001 1.0000
5.250 0.8726 0.01271 0.00539 -0.0629 0.3695 1.0000
5.500 0.8939 0.01317 0.00575 -0.0620 0.3408 1.0000
5.750 0.9151 0.01365 0.00612 -0.0610 0.3154 1.0000
6.000 0.9359 0.01415 0.00651 -0.0600 0.2930 1.0000
6.250 0.9569 0.01463 0.00693 -0.0591 0.2739 1.0000
6.500 0.9778 0.01513 0.00736 -0.0581 0.2565 1.0000
6.750 0.9989 0.01560 0.00782 -0.0572 0.2416 1.0000
7.000 1.0202 0.01605 0.00827 -0.0563 0.2285 1.0000
7.250 1.0412 0.01650 0.00874 -0.0553 0.2162 1.0000
7.500 1.0615 0.01698 0.00922 -0.0543 0.2034 1.0000
7.750 1.0811 0.01749 0.00972 -0.0532 0.1896 1.0000
8.000 1.0996 0.01805 0.01027 -0.0520 0.1732 1.0000
8.250 1.1171 0.01865 0.01082 -0.0506 0.1569 1.0000
8.500 1.1330 0.01930 0.01142 -0.0490 0.1407 1.0000
8.750 1.1487 0.01990 0.01201 -0.0473 0.1283 1.0000
9.000 1.1634 0.02057 0.01267 -0.0455 0.1158 1.0000
9.250 1.1781 0.02125 0.01336 -0.0438 0.1051 1.0000
9.500 1.1921 0.02198 0.01411 -0.0421 0.0955 1.0000
9.750 1.2043 0.02285 0.01496 -0.0402 0.0806 1.0000
10.000 1.2143 0.02391 0.01590 -0.0383 0.0640 1.0000
10.250 1.2243 0.02500 0.01693 -0.0364 0.0511 1.0000
10.500 1.2336 0.02616 0.01806 -0.0346 0.0371 1.0000
10.750 1.2384 0.02772 0.01952 -0.0324 0.0221 1.0000
11.000 1.2425 0.02937 0.02115 -0.0304 0.0142 1.0000
11.250 1.2476 0.03101 0.02283 -0.0285 0.0116 1.0000
11.500 1.2545 0.03252 0.02448 -0.0269 0.0104 1.0000
11.750 1.2604 0.03417 0.02625 -0.0255 0.0095 1.0000
12.000 1.2648 0.03599 0.02824 -0.0241 0.0089 1.0000
12.250 1.2666 0.03812 0.03051 -0.0227 0.0084 1.0000
12.500 1.2674 0.04041 0.03295 -0.0216 0.0081 1.0000
12.750 1.2690 0.04270 0.03540 -0.0207 0.0079 1.0000
13.000 1.2696 0.04517 0.03802 -0.0200 0.0077 1.0000
13.250 1.2696 0.04781 0.04082 -0.0196 0.0073 1.0000
13.500 1.2678 0.05074 0.04392 -0.0193 0.0070 1.0000
13.750 1.2653 0.05389 0.04721 -0.0194 0.0067 1.0000
14.000 1.2619 0.05728 0.05075 -0.0197 0.0064 1.0000
14.250 1.2557 0.06121 0.05484 -0.0204 0.0063 1.0000
14.500 1.2488 0.06546 0.05925 -0.0214 0.0062 1.0000
14.750 1.2411 0.07007 0.06402 -0.0229 0.0061 1.0000
15.000 1.2308 0.07532 0.06944 -0.0248 0.0061 1.0000
15.250 1.2211 0.08075 0.07502 -0.0270 0.0060 1.0000
15.500 1.2072 0.08717 0.08160 -0.0300 0.0058 1.0000
15.750 1.1968 0.09321 0.08780 -0.0328 0.0058 1.0000
16.000 1.1845 0.09983 0.09458 -0.0361 0.0058 1.0000
16.250 1.1711 0.10685 0.10176 -0.0397 0.0058 1.0000
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