NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 50,000 Max Cl/Cd: 19.92 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca24112-jf-50000.txt Download as CSV file: xf-naca24112-jf-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 24112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4616 0.10048 0.09373 0.0186 1.0000 0.3703
-8.250 -0.4610 0.09799 0.09132 0.0202 1.0000 0.3983
-8.000 -0.4659 0.09643 0.08984 0.0223 1.0000 0.4285
-7.750 -0.4419 0.09281 0.08624 0.0247 1.0000 0.4628
-7.500 -0.4055 0.08898 0.08236 0.0270 1.0000 0.5047
-7.250 -0.3900 0.08628 0.07970 0.0296 1.0000 0.5482
-7.000 -0.3650 0.08308 0.07650 0.0311 1.0000 0.5896
-6.750 -0.3625 0.08137 0.07486 0.0341 1.0000 0.6279
-6.000 -0.5351 0.05131 0.04376 -0.0092 1.0000 0.2097
-5.750 -0.5243 0.04707 0.03876 -0.0081 1.0000 0.1821
-5.500 -0.5080 0.04417 0.03558 -0.0065 1.0000 0.1759
-5.250 -0.4927 0.04125 0.03237 -0.0048 1.0000 0.1710
-5.000 -0.4771 0.03945 0.02971 -0.0022 1.0000 0.1631
-4.750 -0.4596 0.03715 0.02713 -0.0005 1.0000 0.1632
-4.500 -0.4413 0.03464 0.02462 0.0008 1.0000 0.1663
-4.250 -0.4221 0.03282 0.02260 0.0023 1.0000 0.1682
-4.000 -0.4024 0.03123 0.02083 0.0038 1.0000 0.1711
-3.750 -0.3830 0.02999 0.01933 0.0053 1.0000 0.1766
-3.500 -0.3626 0.02875 0.01786 0.0066 1.0000 0.1811
-3.250 -0.3412 0.02745 0.01666 0.0075 1.0000 0.1892
-3.000 -0.3195 0.02658 0.01568 0.0084 1.0000 0.1985
-2.500 0.0056 0.02103 0.01295 -0.0257 1.0000 1.0000
-2.000 -0.0164 0.02162 0.01354 -0.0172 1.0000 1.0000
-1.750 -0.0466 0.02240 0.01436 -0.0111 1.0000 1.0000
-1.500 0.0398 0.02264 0.01422 -0.0240 0.9723 1.0000
-1.250 0.1485 0.02226 0.01352 -0.0396 0.9396 1.0000
-1.000 0.2179 0.02188 0.01292 -0.0471 0.8986 1.0000
-0.750 0.2579 0.02171 0.01256 -0.0486 0.8597 1.0000
-0.500 0.2824 0.02177 0.01243 -0.0472 0.8253 1.0000
-0.250 0.3024 0.02195 0.01243 -0.0451 0.7943 1.0000
0.000 0.3220 0.02216 0.01247 -0.0431 0.7678 1.0000
0.250 0.3416 0.02247 0.01263 -0.0413 0.7431 1.0000
0.500 0.3616 0.02275 0.01275 -0.0394 0.7220 1.0000
0.750 0.3824 0.02314 0.01300 -0.0380 0.7021 1.0000
1.000 0.4032 0.02360 0.01337 -0.0367 0.6832 1.0000
1.250 0.4240 0.02408 0.01375 -0.0354 0.6660 1.0000
1.500 0.4449 0.02458 0.01414 -0.0341 0.6505 1.0000
1.750 0.4661 0.02506 0.01452 -0.0327 0.6364 1.0000
2.000 0.4866 0.02573 0.01516 -0.0318 0.6215 1.0000
2.250 0.5069 0.02648 0.01589 -0.0308 0.6077 1.0000
2.500 0.5270 0.02726 0.01665 -0.0298 0.5951 1.0000
2.750 0.5481 0.02788 0.01719 -0.0285 0.5840 1.0000
3.000 0.5679 0.02873 0.01807 -0.0274 0.5721 1.0000
3.250 0.5862 0.02982 0.01920 -0.0266 0.5604 1.0000
3.500 0.6075 0.03050 0.01982 -0.0252 0.5509 1.0000
3.750 0.6247 0.03171 0.02111 -0.0243 0.5397 1.0000
4.000 0.6418 0.03298 0.02244 -0.0232 0.5296 1.0000
4.250 0.6629 0.03375 0.02318 -0.0219 0.5205 1.0000
4.500 0.6750 0.03562 0.02519 -0.0210 0.5102 1.0000
4.750 0.6996 0.03609 0.02560 -0.0195 0.5024 1.0000
5.000 0.7053 0.03859 0.02830 -0.0186 0.4917 1.0000
5.250 0.7248 0.03969 0.02940 -0.0173 0.4838 1.0000
5.500 0.7300 0.04225 0.03211 -0.0163 0.4742 1.0000
5.750 0.7446 0.04389 0.03380 -0.0150 0.4661 1.0000
6.000 0.7458 0.04693 0.03698 -0.0140 0.4573 1.0000
6.250 0.7580 0.04895 0.03905 -0.0129 0.4497 1.0000
6.500 0.7425 0.05378 0.04400 -0.0126 0.4416 1.0000
6.750 0.7631 0.05505 0.04531 -0.0113 0.4341 1.0000
7.000 0.7056 0.06452 0.05479 -0.0134 0.4306 1.0000
7.250 0.6709 0.07105 0.06127 -0.0144 0.4290 1.0000
7.500 0.6537 0.07624 0.06643 -0.0155 0.4284 1.0000
7.750 0.6427 0.08126 0.07146 -0.0168 0.4310 1.0000
8.000 0.6413 0.08572 0.07597 -0.0179 0.4334 1.0000
8.250 0.6549 0.08982 0.08014 -0.0190 0.4359 1.0000
9.750 0.5986 0.11591 0.10638 -0.0273 0.4729 1.0000
10.750 0.6222 0.12788 0.11852 -0.0271 0.4258 1.0000
11.000 0.6360 0.13194 0.12266 -0.0275 0.4171 1.0000
11.250 0.6681 0.13711 0.12796 -0.0278 0.4030 1.0000
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