NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M24 AIRFOIL (m24-il) Reynolds number: 200,000 Max Cl/Cd: 71.21 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m24-il-200000-n5.txt Download as CSV file: xf-m24-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M24 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3027 0.09994 0.09557 -0.0060 0.6410 0.0336
-8.000 -0.3058 0.09671 0.09231 -0.0119 0.6377 0.0340
-7.750 -0.3066 0.09369 0.08924 -0.0167 0.6344 0.0342
-7.500 -0.2988 0.08964 0.08519 -0.0179 0.6302 0.0344
-7.250 -0.2878 0.08615 0.08168 -0.0167 0.6257 0.0348
-7.000 -0.2775 0.08308 0.07857 -0.0171 0.6218 0.0352
-6.750 -0.2667 0.08013 0.07556 -0.0182 0.6180 0.0357
-6.500 -0.2546 0.07717 0.07257 -0.0197 0.6136 0.0363
-6.250 -0.2415 0.07419 0.06953 -0.0214 0.6096 0.0372
-6.000 -0.2271 0.07119 0.06643 -0.0232 0.6060 0.0383
-5.500 -0.1838 0.06445 0.05926 -0.0305 0.5990 0.0414
-5.250 -0.1712 0.06115 0.05595 -0.0301 0.5947 0.0418
-5.000 -0.1553 0.05852 0.05327 -0.0300 0.5908 0.0423
-4.750 -0.1374 0.05611 0.05075 -0.0302 0.5874 0.0431
-4.500 -0.1175 0.05372 0.04828 -0.0307 0.5833 0.0440
-4.250 -0.0960 0.05133 0.04578 -0.0312 0.5790 0.0454
-4.000 -0.0616 0.04906 0.04305 -0.0328 0.5753 0.0492
-3.750 -0.0441 0.04576 0.03962 -0.0326 0.5721 0.0498
-3.500 -0.0257 0.04369 0.03753 -0.0323 0.5683 0.0506
-3.250 -0.0041 0.04186 0.03564 -0.0323 0.5639 0.0517
-3.000 0.0251 0.03647 0.02964 -0.0313 0.5608 0.0415
-2.750 0.0461 0.03521 0.02835 -0.0311 0.5569 0.0401
-2.500 0.0697 0.03320 0.02614 -0.0307 0.5536 0.0389
-2.250 0.0949 0.03088 0.02359 -0.0302 0.5495 0.0378
-2.000 0.1208 0.02870 0.02115 -0.0296 0.5455 0.0377
-1.750 0.1471 0.02669 0.01884 -0.0290 0.5418 0.0383
-1.500 0.1736 0.02440 0.01616 -0.0283 0.5387 0.0375
-1.250 0.2013 0.02225 0.01363 -0.0278 0.5348 0.0369
-1.000 0.2298 0.02069 0.01175 -0.0275 0.5306 0.0368
-0.750 0.2585 0.01959 0.01039 -0.0275 0.5266 0.0370
-0.500 0.2872 0.01876 0.00931 -0.0275 0.5231 0.0373
-0.250 0.3162 0.01810 0.00851 -0.0276 0.5191 0.0378
0.000 0.3450 0.01761 0.00793 -0.0278 0.5148 0.0389
0.250 0.3735 0.01720 0.00741 -0.0279 0.5108 0.0402
0.500 0.4016 0.01682 0.00691 -0.0279 0.5072 0.0409
0.750 0.4296 0.01648 0.00653 -0.0279 0.5032 0.0412
1.000 0.4568 0.01608 0.00617 -0.0279 0.4989 0.0421
1.250 0.4836 0.01583 0.00593 -0.0277 0.4951 0.0431
1.500 0.5102 0.01566 0.00572 -0.0276 0.4917 0.0444
1.750 0.5369 0.01553 0.00559 -0.0274 0.4878 0.0460
2.000 0.5637 0.01544 0.00551 -0.0273 0.4834 0.0484
2.250 0.5903 0.01535 0.00545 -0.0272 0.4793 0.0531
2.500 0.6167 0.01529 0.00538 -0.0270 0.4760 0.0600
2.750 0.6427 0.01523 0.00538 -0.0267 0.4725 0.0823
3.000 0.6685 0.01518 0.00548 -0.0265 0.4683 0.1274
3.250 0.6942 0.01511 0.00557 -0.0263 0.4642 0.1955
3.750 0.8743 0.01463 0.00663 -0.0527 0.4533 0.9968
4.000 0.9134 0.01474 0.00672 -0.0554 0.4491 1.0000
4.250 0.9388 0.01488 0.00679 -0.0552 0.4456 1.0000
4.500 0.9640 0.01503 0.00688 -0.0550 0.4422 1.0000
4.750 0.9892 0.01520 0.00709 -0.0548 0.4378 1.0000
5.000 1.0142 0.01536 0.00726 -0.0546 0.4338 1.0000
5.250 1.0389 0.01554 0.00741 -0.0543 0.4305 1.0000
5.500 1.0635 0.01573 0.00755 -0.0539 0.4276 1.0000
5.750 1.0879 0.01595 0.00784 -0.0537 0.4238 1.0000
6.000 1.1121 0.01616 0.00810 -0.0534 0.4199 1.0000
6.250 1.1360 0.01637 0.00833 -0.0530 0.4162 1.0000
6.500 1.1598 0.01659 0.00852 -0.0526 0.4130 1.0000
6.750 1.1833 0.01684 0.00883 -0.0522 0.4095 1.0000
7.000 1.2064 0.01712 0.00919 -0.0518 0.4059 1.0000
7.250 1.2293 0.01738 0.00951 -0.0513 0.4025 1.0000
7.500 1.2521 0.01765 0.00980 -0.0507 0.3995 1.0000
7.750 1.2748 0.01792 0.01006 -0.0501 0.3967 1.0000
8.000 1.2962 0.01825 0.01053 -0.0495 0.3922 1.0000
8.250 1.3171 0.01854 0.01089 -0.0488 0.3869 1.0000
8.500 1.3380 0.01879 0.01111 -0.0479 0.3816 1.0000
8.750 1.3568 0.01913 0.01160 -0.0469 0.3744 1.0000
9.000 1.3754 0.01943 0.01190 -0.0458 0.3673 1.0000
9.250 1.3927 0.01982 0.01238 -0.0445 0.3602 1.0000
9.500 1.4086 0.02021 0.01280 -0.0431 0.3524 1.0000
9.750 1.4223 0.02068 0.01336 -0.0413 0.3433 1.0000
10.000 1.4339 0.02119 0.01388 -0.0393 0.3352 1.0000
10.250 1.4438 0.02178 0.01457 -0.0371 0.3267 1.0000
10.500 1.4477 0.02252 0.01534 -0.0341 0.3167 1.0000
10.750 1.4400 0.02352 0.01634 -0.0295 0.3062 1.0000
11.000 1.4332 0.02477 0.01763 -0.0257 0.2946 1.0000
11.250 1.4280 0.02633 0.01920 -0.0229 0.2816 1.0000
11.500 1.4221 0.02828 0.02116 -0.0205 0.2660 1.0000
11.750 1.4119 0.03085 0.02367 -0.0185 0.2468 1.0000
12.000 1.3967 0.03412 0.02684 -0.0168 0.2213 1.0000
12.250 1.3769 0.03805 0.03067 -0.0153 0.1959 1.0000
12.500 1.3551 0.04240 0.03492 -0.0140 0.1738 1.0000
12.750 1.3327 0.04700 0.03943 -0.0130 0.1525 1.0000
13.000 1.3070 0.05226 0.04458 -0.0124 0.1253 1.0000
13.250 1.2810 0.05788 0.05007 -0.0121 0.0980 1.0000
13.500 1.2592 0.06322 0.05533 -0.0120 0.0807 1.0000
14.000 1.2222 0.07366 0.06562 -0.0124 0.0403 1.0000
14.250 1.2091 0.07840 0.07033 -0.0128 0.0318 1.0000
14.500 1.2022 0.08244 0.07442 -0.0132 0.0283 1.0000
14.750 1.1960 0.08644 0.07848 -0.0136 0.0260 1.0000
15.000 1.1922 0.09016 0.08228 -0.0141 0.0245 1.0000
15.250 1.1894 0.09381 0.08602 -0.0146 0.0233 1.0000
15.500 1.1861 0.09755 0.08986 -0.0151 0.0223 1.0000
15.750 1.1822 0.10139 0.09379 -0.0158 0.0215 1.0000
16.000 1.1776 0.10540 0.09789 -0.0165 0.0208 1.0000
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Polar data table (+)
Polar graphs
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