NACA 0024 (naca0024-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0024 (naca0024-il) Reynolds number: 100,000 Max Cl/Cd: 30.57 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0024-il-100000-n5.txt Download as CSV file: xf-naca0024-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0024
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
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9276 0.09426 0.08607 -0.0498 1.0000 0.1411
-17.250 -0.8979 0.09548 0.08742 -0.0490 1.0000 0.1429
-17.000 -0.8929 0.09309 0.08504 -0.0497 1.0000 0.1457
-16.750 -0.9349 0.08410 0.07579 -0.0529 1.0000 0.1497
-16.500 -0.9599 0.07781 0.06931 -0.0548 1.0000 0.1530
-16.250 -0.9469 0.07666 0.06822 -0.0548 1.0000 0.1556
-16.000 -0.9510 0.07331 0.06482 -0.0556 1.0000 0.1589
-15.750 -0.9690 0.06834 0.05965 -0.0567 1.0000 0.1625
-15.500 -0.9729 0.06522 0.05647 -0.0570 1.0000 0.1656
-15.250 -0.9653 0.06353 0.05481 -0.0570 1.0000 0.1686
-15.000 -0.9680 0.06071 0.05193 -0.0571 1.0000 0.1721
-14.750 -0.9787 0.05713 0.04818 -0.0572 1.0000 0.1760
-14.500 -0.9736 0.05532 0.04638 -0.0569 1.0000 0.1792
-14.250 -0.9687 0.05356 0.04463 -0.0565 1.0000 0.1826
-14.000 -0.9705 0.05122 0.04222 -0.0560 1.0000 0.1866
-13.750 -0.9771 0.04857 0.03941 -0.0552 1.0000 0.1907
-13.500 -0.9672 0.04747 0.03840 -0.0544 1.0000 0.1941
-13.250 -0.9643 0.04585 0.03677 -0.0534 1.0000 0.1980
-13.000 -0.9659 0.04397 0.03479 -0.0520 1.0000 0.2023
-12.750 -0.9641 0.04246 0.03325 -0.0506 1.0000 0.2063
-12.500 -0.9589 0.04133 0.03217 -0.0490 1.0000 0.2102
-12.250 -0.9584 0.04000 0.03082 -0.0470 1.0000 0.2145
-12.000 -0.9614 0.03860 0.02930 -0.0446 1.0000 0.2190
-11.750 -0.9575 0.03771 0.02849 -0.0423 1.0000 0.2229
-11.500 -0.9573 0.03679 0.02759 -0.0395 1.0000 0.2270
-11.250 -0.9603 0.03582 0.02659 -0.0363 1.0000 0.2315
-11.000 -0.9653 0.03491 0.02561 -0.0326 1.0000 0.2359
-10.750 -0.9656 0.03432 0.02511 -0.0291 1.0000 0.2397
-10.500 -0.9713 0.03369 0.02449 -0.0249 1.0000 0.2438
-10.250 -0.9797 0.03308 0.02384 -0.0201 1.0000 0.2482
-10.000 -0.9895 0.03253 0.02324 -0.0150 1.0000 0.2524
-9.750 -0.9750 0.03194 0.02273 -0.0140 0.9965 0.2574
-9.500 -0.9485 0.03120 0.02194 -0.0154 0.9906 0.2648
-9.250 -0.9232 0.03048 0.02120 -0.0163 0.9830 0.2715
-9.000 -0.8944 0.02986 0.02061 -0.0177 0.9769 0.2787
-8.750 -0.8727 0.02920 0.01983 -0.0177 0.9678 0.2864
-8.500 -0.8416 0.02866 0.01939 -0.0192 0.9616 0.2933
-8.250 -0.8192 0.02811 0.01880 -0.0191 0.9523 0.3011
-8.000 -0.7894 0.02755 0.01826 -0.0202 0.9452 0.3087
-7.750 -0.7625 0.02705 0.01777 -0.0206 0.9372 0.3166
-7.500 -0.7384 0.02652 0.01719 -0.0205 0.9276 0.3247
-7.250 -0.7041 0.02599 0.01674 -0.0221 0.9221 0.3329
-7.000 -0.6879 0.02559 0.01628 -0.0203 0.9092 0.3409
-6.750 -0.6554 0.02511 0.01586 -0.0214 0.9027 0.3489
-6.500 -0.6371 0.02477 0.01551 -0.0198 0.8906 0.3569
-6.250 -0.6084 0.02430 0.01503 -0.0201 0.8825 0.3655
-6.000 -0.5867 0.02399 0.01476 -0.0190 0.8715 0.3733
-5.750 -0.5624 0.02358 0.01425 -0.0185 0.8617 0.3827
-5.500 -0.5367 0.02327 0.01404 -0.0180 0.8516 0.3903
-5.250 -0.5139 0.02294 0.01367 -0.0171 0.8406 0.3993
-5.000 -0.4874 0.02260 0.01335 -0.0167 0.8311 0.4079
-4.750 -0.4655 0.02235 0.01311 -0.0155 0.8190 0.4165
-4.500 -0.4390 0.02201 0.01271 -0.0151 0.8097 0.4260
-4.250 -0.4170 0.02182 0.01259 -0.0139 0.7968 0.4342
-4.000 -0.3906 0.02151 0.01217 -0.0135 0.7875 0.4444
-3.750 -0.3684 0.02135 0.01210 -0.0123 0.7742 0.4525
-3.500 -0.3412 0.02108 0.01177 -0.0119 0.7646 0.4626
-3.250 -0.3199 0.02094 0.01166 -0.0106 0.7513 0.4714
-3.000 -0.2921 0.02072 0.01141 -0.0103 0.7414 0.4812
-2.750 -0.2716 0.02060 0.01127 -0.0088 0.7280 0.4908
-2.500 -0.2430 0.02042 0.01109 -0.0086 0.7181 0.5003
-2.250 -0.2234 0.02032 0.01095 -0.0071 0.7048 0.5109
-2.000 -0.1941 0.02017 0.01083 -0.0069 0.6947 0.5199
-1.750 -0.1735 0.02011 0.01076 -0.0055 0.6817 0.5307
-1.500 -0.1453 0.01999 0.01061 -0.0053 0.6716 0.5403
-1.250 -0.1238 0.01995 0.01061 -0.0040 0.6589 0.5508
-1.000 -0.0967 0.01986 0.01047 -0.0035 0.6488 0.5611
-0.750 -0.0743 0.01985 0.01051 -0.0024 0.6363 0.5715
-0.500 -0.0483 0.01978 0.01038 -0.0018 0.6263 0.5823
-0.250 -0.0248 0.01980 0.01046 -0.0008 0.6143 0.5927
0.000 0.0000 0.01976 0.01035 0.0000 0.6040 0.6040
0.250 0.0248 0.01980 0.01046 0.0008 0.5927 0.6143
0.500 0.0483 0.01978 0.01038 0.0018 0.5823 0.6263
0.750 0.0743 0.01985 0.01051 0.0024 0.5715 0.6363
1.000 0.0967 0.01986 0.01047 0.0035 0.5611 0.6488
1.250 0.1238 0.01995 0.01061 0.0040 0.5508 0.6589
1.500 0.1453 0.01999 0.01061 0.0052 0.5403 0.6716
1.750 0.1735 0.02011 0.01076 0.0055 0.5306 0.6817
2.000 0.1942 0.02017 0.01083 0.0069 0.5199 0.6947
2.250 0.2234 0.02032 0.01095 0.0071 0.5109 0.7048
2.500 0.2431 0.02042 0.01109 0.0086 0.5003 0.7181
2.750 0.2717 0.02060 0.01127 0.0088 0.4908 0.7280
3.000 0.2921 0.02072 0.01140 0.0103 0.4812 0.7414
3.250 0.3200 0.02094 0.01166 0.0106 0.4714 0.7513
3.500 0.3412 0.02108 0.01177 0.0119 0.4626 0.7646
3.750 0.3685 0.02135 0.01210 0.0122 0.4525 0.7743
4.000 0.3907 0.02151 0.01217 0.0134 0.4444 0.7876
4.250 0.4170 0.02182 0.01258 0.0139 0.4342 0.7968
4.500 0.4391 0.02201 0.01271 0.0151 0.4260 0.8097
4.750 0.4656 0.02235 0.01311 0.0155 0.4164 0.8190
5.000 0.4875 0.02260 0.01334 0.0167 0.4079 0.8311
5.250 0.5140 0.02294 0.01367 0.0170 0.3993 0.8406
5.500 0.5368 0.02326 0.01403 0.0180 0.3903 0.8517
5.750 0.5625 0.02358 0.01425 0.0184 0.3827 0.8617
6.000 0.5868 0.02399 0.01475 0.0190 0.3733 0.8715
6.250 0.6086 0.02430 0.01502 0.0201 0.3655 0.8825
6.500 0.6373 0.02476 0.01550 0.0198 0.3569 0.8907
6.750 0.6557 0.02510 0.01585 0.0213 0.3489 0.9028
7.000 0.6881 0.02559 0.01627 0.0202 0.3409 0.9093
7.250 0.7044 0.02599 0.01673 0.0220 0.3328 0.9221
7.500 0.7387 0.02651 0.01718 0.0204 0.3247 0.9276
7.750 0.7628 0.02704 0.01776 0.0206 0.3166 0.9374
8.000 0.7898 0.02754 0.01825 0.0201 0.3086 0.9452
8.250 0.8196 0.02810 0.01879 0.0190 0.3010 0.9524
8.500 0.8422 0.02865 0.01938 0.0191 0.2933 0.9616
8.750 0.8733 0.02919 0.01982 0.0176 0.2864 0.9679
9.000 0.8952 0.02985 0.02059 0.0175 0.2787 0.9770
9.250 0.9240 0.03046 0.02118 0.0161 0.2715 0.9831
9.500 0.9493 0.03118 0.02192 0.0153 0.2647 0.9907
9.750 0.9759 0.03192 0.02271 0.0139 0.2574 0.9966
10.000 0.9896 0.03251 0.02321 0.0150 0.2524 1.0000
10.250 0.9798 0.03305 0.02381 0.0201 0.2482 1.0000
10.500 0.9715 0.03366 0.02445 0.0248 0.2438 1.0000
10.750 0.9659 0.03428 0.02507 0.0291 0.2397 1.0000
11.000 0.9656 0.03488 0.02557 0.0326 0.2359 1.0000
11.250 0.9607 0.03579 0.02655 0.0363 0.2315 1.0000
11.500 0.9578 0.03675 0.02755 0.0395 0.2270 1.0000
11.750 0.9582 0.03767 0.02844 0.0422 0.2228 1.0000
12.000 0.9621 0.03856 0.02926 0.0445 0.2190 1.0000
12.250 0.9593 0.03996 0.03077 0.0470 0.2145 1.0000
12.500 0.9599 0.04128 0.03212 0.0489 0.2101 1.0000
12.750 0.9653 0.04240 0.03319 0.0505 0.2063 1.0000
13.000 0.9671 0.04393 0.03475 0.0519 0.2023 1.0000
13.250 0.9658 0.04580 0.03671 0.0532 0.1979 1.0000
13.500 0.9689 0.04740 0.03833 0.0542 0.1940 1.0000
13.750 0.9790 0.04849 0.03932 0.0550 0.1906 1.0000
14.000 0.9723 0.05117 0.04216 0.0557 0.1865 1.0000
14.250 0.9708 0.05348 0.04455 0.0562 0.1826 1.0000
14.500 0.9759 0.05523 0.04628 0.0566 0.1791 1.0000
14.750 0.9805 0.05710 0.04815 0.0570 0.1759 1.0000
15.000 0.9703 0.06063 0.05185 0.0568 0.1720 1.0000
15.250 0.9681 0.06341 0.05469 0.0567 0.1685 1.0000
15.500 0.9760 0.06508 0.05632 0.0568 0.1655 1.0000
15.750 0.9713 0.06830 0.05961 0.0564 0.1624 1.0000
16.000 0.9539 0.07319 0.06469 0.0553 0.1587 1.0000
16.250 0.9505 0.07646 0.06801 0.0546 0.1555 1.0000
16.500 0.9638 0.07759 0.06908 0.0546 0.1529 1.0000
16.750 0.9374 0.08407 0.07576 0.0526 0.1496 1.0000
17.000 0.8981 0.09269 0.08463 0.0494 0.1456 1.0000
17.250 0.9033 0.09506 0.08699 0.0488 0.1429 1.0000
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