NACA 4424 (naca4424-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4424 (naca4424-il) Reynolds number: 100,000 Max Cl/Cd: 33.48 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4424-il-100000-n5.txt Download as CSV file: xf-naca4424-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4424
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.3734 0.16057 0.15414 -0.0472 1.0000 0.0902
-16.500 -0.3746 0.15832 0.15192 -0.0468 1.0000 0.0914
-15.000 -0.7492 0.06893 0.06131 -0.0951 0.9869 0.1215
-14.750 -0.7222 0.06853 0.06100 -0.0962 0.9836 0.1233
-14.500 -0.7241 0.06449 0.05685 -0.0997 0.9801 0.1253
-14.250 -0.7428 0.05928 0.05144 -0.1027 0.9744 0.1275
-14.000 -0.7611 0.05437 0.04622 -0.1056 0.9686 0.1298
-13.750 -0.7542 0.05183 0.04358 -0.1078 0.9649 0.1320
-13.500 -0.7465 0.05040 0.04217 -0.1075 0.9579 0.1339
-13.250 -0.7368 0.04841 0.04010 -0.1089 0.9532 0.1362
-13.000 -0.7392 0.04619 0.03772 -0.1087 0.9463 0.1387
-12.750 -0.7428 0.04390 0.03516 -0.1084 0.9392 0.1413
-12.500 -0.7181 0.04296 0.03431 -0.1098 0.9359 0.1437
-12.250 -0.7165 0.04194 0.03327 -0.1076 0.9269 0.1458
-12.000 -0.7042 0.04062 0.03184 -0.1075 0.9214 0.1487
-11.750 -0.6958 0.03918 0.03019 -0.1069 0.9161 0.1520
-11.500 -0.6928 0.03844 0.02945 -0.1041 0.9066 0.1542
-11.250 -0.6716 0.03760 0.02862 -0.1042 0.9021 0.1571
-11.000 -0.6490 0.03655 0.02748 -0.1047 0.8989 0.1609
-10.750 -0.6609 0.03601 0.02682 -0.0989 0.8860 0.1632
-10.500 -0.6406 0.03515 0.02593 -0.0985 0.8816 0.1665
-10.250 -0.6146 0.03438 0.02516 -0.0989 0.8786 0.1702
-10.000 -0.6276 0.03417 0.02489 -0.0922 0.8652 0.1724
-9.750 -0.6104 0.03334 0.02391 -0.0909 0.8605 0.1766
-9.500 -0.5832 0.03256 0.02315 -0.0912 0.8575 0.1806
-9.250 -0.5939 0.03247 0.02305 -0.0846 0.8443 0.1827
-9.000 -0.5716 0.03177 0.02229 -0.0839 0.8396 0.1871
-8.750 -0.5440 0.03094 0.02133 -0.0841 0.8365 0.1924
-8.500 -0.5493 0.03085 0.02128 -0.0784 0.8244 0.1947
-8.250 -0.5268 0.03027 0.02069 -0.0775 0.8191 0.1993
-8.000 -0.4978 0.02953 0.01981 -0.0777 0.8157 0.2052
-7.750 -0.4969 0.02936 0.01964 -0.0730 0.8051 0.2084
-7.500 -0.4765 0.02889 0.01920 -0.0716 0.7988 0.2130
-7.250 -0.4462 0.02823 0.01845 -0.0720 0.7951 0.2192
-7.000 -0.4336 0.02791 0.01808 -0.0692 0.7872 0.2239
-6.750 -0.4211 0.02764 0.01785 -0.0664 0.7788 0.2281
-6.500 -0.3904 0.02705 0.01720 -0.0668 0.7746 0.2348
-6.250 -0.3528 0.02636 0.01646 -0.0684 0.7716 0.2418
-6.000 -0.3615 0.02652 0.01664 -0.0618 0.7589 0.2450
-5.750 -0.3316 0.02601 0.01610 -0.0619 0.7541 0.2520
-5.500 -0.2931 0.02538 0.01540 -0.0637 0.7507 0.2598
-5.250 -0.2976 0.02550 0.01556 -0.0577 0.7390 0.2637
-5.000 -0.2695 0.02508 0.01510 -0.0576 0.7334 0.2714
-4.750 -0.2309 0.02451 0.01448 -0.0593 0.7295 0.2797
-4.500 -0.2296 0.02458 0.01458 -0.0544 0.7193 0.2846
-4.250 -0.2054 0.02428 0.01423 -0.0535 0.7126 0.2926
-4.000 -0.1677 0.02378 0.01371 -0.0550 0.7082 0.3015
-3.750 -0.1572 0.02374 0.01369 -0.0517 0.6999 0.3080
-3.500 -0.1403 0.02363 0.01352 -0.0495 0.6919 0.3161
-3.250 -0.1054 0.02319 0.01311 -0.0506 0.6869 0.3254
-3.000 -0.0820 0.02300 0.01290 -0.0496 0.6805 0.3344
-2.750 -0.0751 0.02309 0.01295 -0.0456 0.6715 0.3420
-2.500 -0.0446 0.02276 0.01267 -0.0459 0.6659 0.3517
-2.250 -0.0033 0.02237 0.01217 -0.0481 0.6614 0.3645
-2.000 -0.0104 0.02264 0.01256 -0.0417 0.6516 0.3705
-1.750 0.0149 0.02245 0.01237 -0.0410 0.6453 0.3820
-1.500 0.0533 0.02209 0.01199 -0.0427 0.6407 0.3951
-1.250 0.0555 0.02229 0.01225 -0.0379 0.6326 0.4046
-1.000 0.0731 0.02227 0.01223 -0.0359 0.6256 0.4165
-0.750 0.1053 0.02200 0.01199 -0.0364 0.6204 0.4319
-0.500 0.1258 0.02196 0.01199 -0.0349 0.6146 0.4462
-0.250 0.1311 0.02216 0.01226 -0.0308 0.6070 0.4596
0.000 0.1558 0.02203 0.01219 -0.0300 0.6012 0.4777
0.250 0.1926 0.02176 0.01194 -0.0313 0.5968 0.5002
0.500 0.1933 0.02207 0.01235 -0.0264 0.5895 0.5171
0.750 0.2077 0.02217 0.01253 -0.0239 0.5831 0.5390
1.000 0.2366 0.02204 0.01245 -0.0238 0.5780 0.5658
1.250 0.2718 0.02188 0.01234 -0.0249 0.5735 0.5949
1.500 0.2695 0.02230 0.01291 -0.0196 0.5660 0.6172
1.750 0.2919 0.02238 0.01308 -0.0185 0.5601 0.6457
2.000 0.3310 0.02225 0.01302 -0.0203 0.5554 0.6788
2.250 0.3634 0.02233 0.01320 -0.0211 0.5501 0.7120
2.500 0.3797 0.02273 0.01378 -0.0193 0.5432 0.7438
2.750 0.4217 0.02286 0.01399 -0.0220 0.5374 0.7815
3.000 0.4922 0.02288 0.01403 -0.0298 0.5325 0.8182
3.250 0.5373 0.02342 0.01468 -0.0335 0.5258 0.8491
3.500 0.5895 0.02392 0.01523 -0.0386 0.5188 0.8733
3.750 0.6481 0.02417 0.01542 -0.0443 0.5132 0.8926
4.000 0.6969 0.02450 0.01569 -0.0483 0.5079 0.9096
4.250 0.7215 0.02522 0.01648 -0.0484 0.5007 0.9283
4.500 0.7569 0.02563 0.01685 -0.0501 0.4947 0.9459
4.750 0.8021 0.02583 0.01693 -0.0533 0.4898 0.9615
5.000 0.8289 0.02653 0.01767 -0.0542 0.4834 0.9785
5.250 0.8648 0.02712 0.01827 -0.0566 0.4764 0.9918
5.500 0.9160 0.02736 0.01841 -0.0614 0.4707 1.0000
5.750 0.9220 0.02755 0.01854 -0.0580 0.4661 1.0000
6.000 0.9037 0.02824 0.01927 -0.0510 0.4602 1.0000
6.250 0.9048 0.02867 0.01969 -0.0470 0.4548 1.0000
6.500 0.9213 0.02882 0.01975 -0.0452 0.4502 1.0000
6.750 0.9290 0.02924 0.02012 -0.0423 0.4452 1.0000
7.000 0.9173 0.03023 0.02117 -0.0367 0.4391 1.0000
7.250 0.9248 0.03073 0.02165 -0.0339 0.4337 1.0000
7.500 0.9477 0.03078 0.02160 -0.0331 0.4291 1.0000
7.750 0.9414 0.03184 0.02270 -0.0287 0.4233 1.0000
8.000 0.9369 0.03292 0.02383 -0.0247 0.4171 1.0000
8.250 0.9522 0.03328 0.02414 -0.0231 0.4121 1.0000
8.500 0.9755 0.03338 0.02414 -0.0224 0.4078 1.0000
8.750 0.9538 0.03539 0.02629 -0.0170 0.4007 1.0000
9.000 0.9608 0.03621 0.02710 -0.0147 0.3951 1.0000
9.250 0.9869 0.03613 0.02692 -0.0143 0.3906 1.0000
9.500 0.9720 0.03818 0.02908 -0.0102 0.3840 1.0000
9.750 0.9701 0.03964 0.03058 -0.0075 0.3777 1.0000
10.000 0.9923 0.03974 0.03060 -0.0069 0.3731 1.0000
10.250 0.9877 0.04151 0.03242 -0.0042 0.3671 1.0000
10.500 0.9775 0.04375 0.03474 -0.0014 0.3602 1.0000
10.750 0.9982 0.04393 0.03486 -0.0006 0.3555 1.0000
11.000 0.9997 0.04552 0.03647 0.0012 0.3498 1.0000
11.250 0.9821 0.04862 0.03968 0.0039 0.3422 1.0000
11.500 1.0037 0.04874 0.03974 0.0044 0.3377 1.0000
11.750 0.9990 0.05103 0.04208 0.0062 0.3315 1.0000
12.000 0.9845 0.05428 0.04542 0.0080 0.3241 1.0000
12.250 1.0095 0.05409 0.04516 0.0085 0.3200 1.0000
12.500 0.9882 0.05818 0.04935 0.0102 0.3125 1.0000
12.750 0.9855 0.06063 0.05184 0.0112 0.3059 1.0000
13.000 1.0157 0.05987 0.05101 0.0115 0.3024 1.0000
13.250 0.9723 0.06664 0.05796 0.0130 0.2928 1.0000
13.500 0.9891 0.06721 0.05849 0.0135 0.2881 1.0000
13.750 1.0236 0.06588 0.05707 0.0138 0.2851 1.0000
14.000 0.9663 0.07471 0.06612 0.0145 0.2743 1.0000
14.250 0.9925 0.07422 0.06557 0.0150 0.2709 1.0000
14.750 0.9642 0.08280 0.07430 0.0153 0.2569 1.0000
15.000 0.9965 0.08148 0.07291 0.0158 0.2544 1.0000
15.250 0.9391 0.09148 0.08309 0.0150 0.2432 1.0000
15.500 0.9665 0.09065 0.08222 0.0155 0.2404 1.0000
15.750 1.0010 0.08893 0.08043 0.0161 0.2384 1.0000
16.250 0.9670 0.09901 0.09066 0.0151 0.2247 1.0000
16.500 1.0033 0.09694 0.08851 0.0157 0.2231 1.0000
17.000 0.9687 0.10741 0.09914 0.0141 0.2098 1.0000
17.500 0.9357 0.11816 0.11004 0.0118 0.1967 1.0000
17.750 0.9688 0.11624 0.10806 0.0125 0.1955 1.0000
18.250 0.9358 0.12727 0.11924 0.0096 0.1828 1.0000
18.750 0.9078 0.13799 0.13007 0.0062 0.1705 1.0000
19.000 0.9353 0.13666 0.12871 0.0068 0.1697 1.0000
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Polar data table (+)
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