NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M24 AIRFOIL (m24-il) Reynolds number: 500,000 Max Cl/Cd: 104.16 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m24-il-500000.txt Download as CSV file: xf-m24-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2239 0.08768 0.08449 -0.0106 0.6241 0.0249
-8.000 -0.2197 0.08453 0.08131 -0.0114 0.6205 0.0251
-7.750 -0.2163 0.08133 0.07808 -0.0124 0.6171 0.0255
-7.500 -0.2140 0.07796 0.07473 -0.0138 0.6137 0.0258
-7.250 -0.2132 0.07448 0.07127 -0.0157 0.6102 0.0262
-7.000 -0.2139 0.07097 0.06773 -0.0176 0.6069 0.0266
-6.750 -0.2145 0.06765 0.06438 -0.0186 0.6037 0.0271
-6.500 -0.2098 0.06388 0.06056 -0.0206 0.6006 0.0279
-6.250 -0.2026 0.05894 0.05549 -0.0264 0.5980 0.0288
-6.000 -0.1906 0.05459 0.05104 -0.0285 0.5947 0.0289
-5.750 -0.1850 0.04995 0.04639 -0.0280 0.5913 0.0292
-5.500 -0.1726 0.04696 0.04334 -0.0278 0.5877 0.0295
-5.250 -0.1585 0.04419 0.04051 -0.0279 0.5840 0.0298
-5.000 -0.1429 0.04134 0.03762 -0.0282 0.5802 0.0302
-4.750 -0.1261 0.03850 0.03472 -0.0286 0.5763 0.0309
-4.500 -0.1081 0.03564 0.03175 -0.0291 0.5728 0.0317
-4.250 -0.0880 0.03269 0.02863 -0.0296 0.5695 0.0333
-4.000 -0.0635 0.02787 0.02349 -0.0302 0.5668 0.0347
-3.750 -0.0474 0.02550 0.02111 -0.0299 0.5629 0.0352
-3.500 -0.0280 0.02367 0.01923 -0.0296 0.5589 0.0356
-3.250 -0.0074 0.02193 0.01738 -0.0294 0.5553 0.0363
-3.000 0.0144 0.02017 0.01548 -0.0291 0.5518 0.0374
-2.750 0.0464 0.01815 0.01307 -0.0283 0.5485 0.0411
-2.500 0.0620 0.01515 0.00999 -0.0276 0.5450 0.0420
-2.250 0.0842 0.01405 0.00882 -0.0274 0.5411 0.0426
-2.000 0.1074 0.01306 0.00770 -0.0271 0.5376 0.0436
-1.750 0.1321 0.01202 0.00656 -0.0268 0.5340 0.0456
-1.500 0.1577 0.01024 0.00442 -0.0256 0.5307 0.0503
-1.250 0.1822 0.00958 0.00372 -0.0255 0.5266 0.0514
-1.000 0.2075 0.00897 0.00299 -0.0253 0.5230 0.0533
-0.750 0.2342 0.00800 0.00164 -0.0244 0.5198 0.0600
-0.500 0.2601 0.00747 0.00111 -0.0245 0.5160 0.0614
-0.250 0.2966 0.01537 0.00779 -0.0224 0.5168 0.0418
0.000 0.3256 0.01503 0.00737 -0.0225 0.5127 0.0412
0.250 0.3546 0.01429 0.00651 -0.0226 0.5087 0.0413
0.500 0.3833 0.01386 0.00595 -0.0227 0.5048 0.0411
0.750 0.4122 0.01318 0.00526 -0.0229 0.5012 0.0409
1.000 0.4405 0.01278 0.00484 -0.0229 0.4972 0.0411
1.250 0.4675 0.01225 0.00427 -0.0227 0.4934 0.0418
1.500 0.4941 0.01199 0.00397 -0.0225 0.4896 0.0428
1.750 0.5214 0.01179 0.00381 -0.0224 0.4857 0.0441
2.000 0.5488 0.01165 0.00369 -0.0224 0.4816 0.0456
2.250 0.5763 0.01158 0.00361 -0.0223 0.4778 0.0481
2.500 0.6032 0.01152 0.00351 -0.0222 0.4741 0.0512
2.750 0.6308 0.01146 0.00349 -0.0223 0.4704 0.0573
3.000 0.6576 0.01130 0.00353 -0.0221 0.4664 0.1117
3.250 0.6842 0.01119 0.00360 -0.0221 0.4624 0.1943
3.500 0.7083 0.00974 0.00397 -0.0213 0.4587 0.9532
3.750 0.7840 0.01035 0.00456 -0.0315 0.4535 0.9786
4.000 0.8898 0.01078 0.00491 -0.0484 0.4473 0.9959
4.250 0.9405 0.01089 0.00493 -0.0537 0.4428 1.0000
4.500 0.9670 0.01096 0.00501 -0.0537 0.4391 1.0000
4.750 0.9935 0.01102 0.00509 -0.0537 0.4350 1.0000
5.000 1.0197 0.01111 0.00515 -0.0537 0.4311 1.0000
5.250 1.0459 0.01127 0.00526 -0.0537 0.4273 1.0000
5.500 1.0721 0.01137 0.00539 -0.0537 0.4239 1.0000
5.750 1.0981 0.01147 0.00551 -0.0536 0.4201 1.0000
6.000 1.1240 0.01158 0.00563 -0.0536 0.4165 1.0000
6.250 1.1496 0.01176 0.00577 -0.0535 0.4129 1.0000
6.500 1.1752 0.01191 0.00595 -0.0534 0.4092 1.0000
6.750 1.2006 0.01201 0.00610 -0.0533 0.4048 1.0000
7.000 1.2256 0.01214 0.00623 -0.0532 0.3995 1.0000
7.250 1.2503 0.01232 0.00641 -0.0530 0.3941 1.0000
7.500 1.2751 0.01244 0.00659 -0.0528 0.3893 1.0000
7.750 1.2993 0.01261 0.00677 -0.0525 0.3843 1.0000
8.000 1.3229 0.01279 0.00697 -0.0522 0.3776 1.0000
8.250 1.3466 0.01295 0.00716 -0.0519 0.3703 1.0000
8.500 1.3694 0.01320 0.00740 -0.0514 0.3641 1.0000
8.750 1.3926 0.01337 0.00765 -0.0511 0.3575 1.0000
9.000 1.4142 0.01366 0.00793 -0.0505 0.3487 1.0000
9.250 1.4357 0.01393 0.00822 -0.0499 0.3386 1.0000
9.500 1.4562 0.01424 0.00856 -0.0491 0.3276 1.0000
9.750 1.4746 0.01469 0.00899 -0.0481 0.3128 1.0000
10.000 1.4889 0.01536 0.00958 -0.0466 0.2921 1.0000
10.250 1.4937 0.01651 0.01054 -0.0439 0.2551 1.0000
10.500 1.4757 0.01855 0.01228 -0.0381 0.2063 1.0000
10.750 1.4477 0.02023 0.01391 -0.0306 0.1892 1.0000
11.000 1.4207 0.02282 0.01639 -0.0250 0.1661 1.0000
11.250 1.3954 0.02618 0.01962 -0.0211 0.1391 1.0000
11.500 1.3675 0.03038 0.02368 -0.0182 0.1050 1.0000
11.750 1.3425 0.03478 0.02796 -0.0162 0.0801 1.0000
12.000 1.3213 0.03910 0.03222 -0.0147 0.0571 1.0000
12.250 1.2984 0.04377 0.03680 -0.0135 0.0360 1.0000
12.500 1.2875 0.04744 0.04048 -0.0128 0.0293 1.0000
12.750 1.2812 0.05082 0.04391 -0.0124 0.0262 1.0000
13.000 1.2794 0.05378 0.04695 -0.0122 0.0248 1.0000
13.250 1.2765 0.05694 0.05019 -0.0120 0.0238 1.0000
13.500 1.2724 0.06031 0.05363 -0.0119 0.0228 1.0000
13.750 1.2664 0.06394 0.05735 -0.0119 0.0219 1.0000
14.000 1.2608 0.06762 0.06112 -0.0120 0.0213 1.0000
14.250 1.2587 0.07094 0.06452 -0.0121 0.0209 1.0000
14.500 1.2556 0.07439 0.06806 -0.0123 0.0205 1.0000
14.750 1.2521 0.07794 0.07169 -0.0126 0.0200 1.0000
15.000 1.2480 0.08163 0.07545 -0.0130 0.0195 1.0000
15.250 1.2438 0.08536 0.07925 -0.0134 0.0191 1.0000
15.500 1.2389 0.08921 0.08318 -0.0138 0.0186 1.0000
15.750 1.2328 0.09327 0.08731 -0.0144 0.0182 1.0000
16.000 1.2254 0.09753 0.09163 -0.0150 0.0178 1.0000
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