AG37 (ag37-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.92 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag37-il-1000000.txt Download as CSV file: xf-ag37-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG37
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5201 0.08709 0.08552 -0.0049 1.0000 0.0111
-9.250 -0.5196 0.08259 0.08104 -0.0081 1.0000 0.0114
-9.000 -0.5169 0.07679 0.07526 -0.0147 1.0000 0.0118
-8.750 -0.5063 0.07040 0.06885 -0.0225 1.0000 0.0121
-8.500 -0.4946 0.06413 0.06253 -0.0289 1.0000 0.0121
-8.250 -0.4826 0.05764 0.05596 -0.0341 1.0000 0.0122
-8.000 -0.4715 0.05112 0.04931 -0.0375 1.0000 0.0122
-7.750 -0.5010 0.02485 0.02174 -0.0409 1.0000 0.0089
-7.500 -0.4892 0.01857 0.01467 -0.0397 1.0000 0.0092
-7.250 -0.4684 0.01710 0.01300 -0.0388 1.0000 0.0095
-7.000 -0.4463 0.01622 0.01200 -0.0378 1.0000 0.0098
-6.750 -0.4191 0.01506 0.01067 -0.0378 0.9995 0.0101
-6.500 -0.3856 0.01378 0.00919 -0.0391 0.9981 0.0104
-6.250 -0.3515 0.01260 0.00783 -0.0404 0.9966 0.0108
-6.000 -0.3168 0.01165 0.00674 -0.0418 0.9952 0.0113
-5.750 -0.2816 0.01116 0.00618 -0.0433 0.9934 0.0120
-5.500 -0.2485 0.00995 0.00484 -0.0444 0.9908 0.0129
-5.250 -0.2130 0.00938 0.00424 -0.0460 0.9881 0.0140
-5.000 -0.1766 0.00896 0.00380 -0.0478 0.9852 0.0151
-4.750 -0.1432 0.00861 0.00341 -0.0488 0.9803 0.0162
-4.500 -0.1122 0.00811 0.00285 -0.0493 0.9728 0.0175
-4.250 -0.0832 0.00780 0.00253 -0.0494 0.9625 0.0200
-4.000 -0.0555 0.00759 0.00229 -0.0491 0.9502 0.0219
-3.750 -0.0291 0.00731 0.00194 -0.0484 0.9339 0.0247
-3.500 -0.0033 0.00712 0.00171 -0.0477 0.9106 0.0296
-3.250 0.0215 0.00698 0.00146 -0.0466 0.8635 0.0404
-3.000 0.0474 0.00684 0.00130 -0.0460 0.8291 0.0799
-2.750 0.0743 0.00661 0.00120 -0.0458 0.8026 0.1477
-2.500 0.1014 0.00632 0.00112 -0.0457 0.7783 0.2452
-2.250 0.1286 0.00607 0.00107 -0.0457 0.7530 0.3449
-2.000 0.1555 0.00570 0.00104 -0.0457 0.7253 0.4884
-1.750 0.1814 0.00520 0.00103 -0.0455 0.6885 0.6835
-1.500 0.2007 0.00477 0.00106 -0.0433 0.6286 0.8955
-1.250 0.2327 0.00479 0.00103 -0.0438 0.5947 0.9901
-1.000 0.2648 0.00491 0.00103 -0.0448 0.5734 1.0000
-0.750 0.2924 0.00502 0.00104 -0.0447 0.5573 1.0000
-0.500 0.3202 0.00512 0.00105 -0.0446 0.5431 1.0000
-0.250 0.3481 0.00522 0.00107 -0.0446 0.5303 1.0000
0.000 0.3760 0.00531 0.00110 -0.0446 0.5182 1.0000
0.250 0.4040 0.00541 0.00113 -0.0446 0.5060 1.0000
0.500 0.4319 0.00551 0.00117 -0.0446 0.4933 1.0000
0.750 0.4600 0.00560 0.00122 -0.0446 0.4800 1.0000
1.000 0.4880 0.00571 0.00126 -0.0446 0.4650 1.0000
1.250 0.5160 0.00581 0.00131 -0.0447 0.4467 1.0000
1.500 0.5438 0.00596 0.00137 -0.0447 0.4247 1.0000
1.750 0.5715 0.00612 0.00145 -0.0447 0.4007 1.0000
2.000 0.5991 0.00632 0.00154 -0.0448 0.3767 1.0000
2.250 0.6265 0.00653 0.00165 -0.0448 0.3516 1.0000
2.500 0.6540 0.00674 0.00177 -0.0448 0.3277 1.0000
2.750 0.6814 0.00697 0.00191 -0.0449 0.3046 1.0000
3.000 0.7087 0.00719 0.00205 -0.0449 0.2825 1.0000
3.250 0.7360 0.00744 0.00221 -0.0449 0.2593 1.0000
3.500 0.7630 0.00772 0.00239 -0.0450 0.2348 1.0000
3.750 0.7900 0.00799 0.00258 -0.0450 0.2109 1.0000
4.000 0.8168 0.00830 0.00278 -0.0450 0.1870 1.0000
4.250 0.8433 0.00866 0.00303 -0.0450 0.1594 1.0000
4.500 0.8695 0.00904 0.00330 -0.0449 0.1334 1.0000
4.750 0.8955 0.00947 0.00360 -0.0448 0.1073 1.0000
5.000 0.9213 0.00993 0.00394 -0.0448 0.0837 1.0000
5.250 0.9471 0.01036 0.00428 -0.0447 0.0661 1.0000
5.500 0.9728 0.01080 0.00466 -0.0445 0.0521 1.0000
5.750 0.9987 0.01120 0.00503 -0.0444 0.0430 1.0000
6.000 1.0246 0.01158 0.00541 -0.0443 0.0369 1.0000
6.250 1.0497 0.01208 0.00589 -0.0441 0.0309 1.0000
6.500 1.0756 0.01242 0.00627 -0.0440 0.0284 1.0000
6.750 1.1011 0.01282 0.00668 -0.0438 0.0256 1.0000
7.000 1.1248 0.01351 0.00742 -0.0434 0.0221 1.0000
7.250 1.1505 0.01382 0.00777 -0.0433 0.0211 1.0000
7.500 1.1756 0.01421 0.00819 -0.0431 0.0194 1.0000
7.750 1.1995 0.01477 0.00878 -0.0428 0.0176 1.0000
8.000 1.2213 0.01562 0.00973 -0.0421 0.0160 1.0000
8.250 1.2460 0.01601 0.01017 -0.0419 0.0153 1.0000
8.500 1.2700 0.01645 0.01065 -0.0416 0.0142 1.0000
8.750 1.2934 0.01695 0.01118 -0.0413 0.0132 1.0000
9.000 1.3127 0.01801 0.01233 -0.0404 0.0119 1.0000
9.250 1.3335 0.01879 0.01322 -0.0397 0.0114 1.0000
9.500 1.3558 0.01934 0.01383 -0.0392 0.0109 1.0000
9.750 1.3775 0.01993 0.01448 -0.0387 0.0102 1.0000
10.000 1.3990 0.02050 0.01510 -0.0382 0.0096 1.0000
10.250 1.4181 0.02132 0.01597 -0.0374 0.0089 1.0000
10.500 1.4282 0.02306 0.01788 -0.0354 0.0082 1.0000
10.750 1.4474 0.02373 0.01864 -0.0346 0.0080 1.0000
11.000 1.4647 0.02456 0.01956 -0.0336 0.0076 1.0000
11.250 1.4801 0.02548 0.02059 -0.0324 0.0073 1.0000
11.500 1.4942 0.02645 0.02164 -0.0310 0.0070 1.0000
11.750 1.5063 0.02746 0.02274 -0.0295 0.0067 1.0000
12.000 1.5136 0.02853 0.02389 -0.0272 0.0064 1.0000
12.250 1.5161 0.02997 0.02543 -0.0247 0.0062 1.0000
12.500 1.5122 0.03207 0.02767 -0.0221 0.0060 1.0000
12.750 1.4993 0.03531 0.03109 -0.0200 0.0058 1.0000
13.250 1.4811 0.04282 0.03895 -0.0202 0.0056 1.0000
13.500 1.4773 0.04660 0.04288 -0.0214 0.0055 1.0000
13.750 1.4716 0.05105 0.04748 -0.0235 0.0055 1.0000
14.000 1.4620 0.05645 0.05304 -0.0263 0.0054 1.0000
14.250 1.4493 0.06241 0.05916 -0.0293 0.0054 1.0000
14.500 1.4318 0.06919 0.06609 -0.0326 0.0054 1.0000
14.750 1.4112 0.07651 0.07355 -0.0361 0.0054 1.0000
15.000 1.3887 0.08435 0.08153 -0.0398 0.0054 1.0000
15.250 1.3631 0.09281 0.09012 -0.0437 0.0054 1.0000
15.500 1.3374 0.10165 0.09909 -0.0478 0.0054 1.0000
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Polar data table (+)
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