NACA 65(4)-421 (naca654421-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(4)-421 (naca654421-il) Reynolds number: 200,000 Max Cl/Cd: 53.9 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca654421-il-200000.txt Download as CSV file: xf-naca654421-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(4)-421
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7181 0.07777 0.07306 -0.0967 1.0000 0.0540
-15.500 -0.7290 0.07349 0.06870 -0.0970 1.0000 0.0537
-15.250 -0.7483 0.06962 0.06473 -0.0966 1.0000 0.0535
-15.000 -0.7760 0.06700 0.06204 -0.0944 1.0000 0.0534
-14.750 -0.7925 0.06377 0.05869 -0.0940 0.9948 0.0531
-14.500 -0.7963 0.05909 0.05375 -0.0970 0.9866 0.0529
-14.250 -0.7967 0.05474 0.04910 -0.1000 0.9804 0.0528
-14.000 -0.7894 0.05093 0.04500 -0.1026 0.9740 0.0526
-13.750 -0.7777 0.04745 0.04121 -0.1053 0.9679 0.0527
-13.500 -0.7641 0.04459 0.03803 -0.1075 0.9601 0.0530
-13.250 -0.7459 0.04206 0.03520 -0.1096 0.9522 0.0534
-13.000 -0.7247 0.03989 0.03274 -0.1112 0.9440 0.0537
-12.750 -0.7043 0.03812 0.03071 -0.1119 0.9343 0.0539
-12.500 -0.6793 0.03655 0.02892 -0.1127 0.9263 0.0541
-12.250 -0.6322 0.03478 0.02711 -0.1146 0.9210 0.0548
-12.000 -0.5976 0.03379 0.02614 -0.1153 0.9131 0.0559
-11.750 -0.5726 0.03301 0.02530 -0.1152 0.9048 0.0571
-11.500 -0.5466 0.03231 0.02451 -0.1149 0.8962 0.0579
-11.250 -0.5191 0.03167 0.02378 -0.1148 0.8896 0.0589
-11.000 -0.4946 0.03113 0.02320 -0.1142 0.8814 0.0598
-10.750 -0.4711 0.03062 0.02258 -0.1135 0.8746 0.0608
-10.500 -0.4484 0.03015 0.02207 -0.1128 0.8674 0.0618
-10.250 -0.4263 0.02963 0.02162 -0.1119 0.8603 0.0632
-10.000 -0.4095 0.02903 0.02101 -0.1108 0.8542 0.0649
-9.750 -0.3957 0.02842 0.02040 -0.1095 0.8469 0.0671
-9.500 -0.3815 0.02779 0.01971 -0.1083 0.8403 0.0693
-9.250 -0.3714 0.02694 0.01885 -0.1067 0.8350 0.0718
-9.000 -0.3633 0.02613 0.01807 -0.1051 0.8283 0.0749
-8.750 -0.3537 0.02535 0.01724 -0.1035 0.8221 0.0787
-8.500 -0.3492 0.02430 0.01619 -0.1014 0.8168 0.0835
-8.250 -0.3449 0.02339 0.01530 -0.0993 0.8107 0.0915
-8.000 -0.3472 0.02217 0.01423 -0.0964 0.8045 0.1073
-7.750 -0.3583 0.02059 0.01293 -0.0925 0.7992 0.1514
-7.500 -0.3781 0.01904 0.01173 -0.0872 0.7938 0.2138
-7.250 -0.4023 0.01811 0.01110 -0.0804 0.7870 0.2659
-7.000 -0.4215 0.01693 0.01037 -0.0740 0.7819 0.3509
-6.750 -0.4228 0.01630 0.01038 -0.0696 0.7783 0.4736
-6.500 -0.4057 0.01655 0.01068 -0.0679 0.7736 0.5217
-6.250 -0.3829 0.01696 0.01109 -0.0669 0.7690 0.5459
-6.000 -0.3577 0.01733 0.01138 -0.0662 0.7654 0.5633
-5.750 -0.3312 0.01769 0.01164 -0.0658 0.7625 0.5774
-5.500 -0.3043 0.01803 0.01184 -0.0655 0.7600 0.5904
-5.250 -0.2726 0.01905 0.01293 -0.0650 0.7571 0.6011
-5.000 -0.2476 0.01998 0.01388 -0.0639 0.7527 0.6138
-4.750 -0.2149 0.02127 0.01521 -0.0632 0.7491 0.6245
-4.500 -0.1822 0.02222 0.01615 -0.0628 0.7461 0.6324
-4.250 -0.1385 0.02378 0.01770 -0.0631 0.7439 0.6368
-4.000 -0.1234 0.02329 0.01706 -0.0622 0.7414 0.6482
-3.750 -0.0899 0.02398 0.01773 -0.0621 0.7391 0.6504
-3.500 -0.0635 0.02462 0.01841 -0.0614 0.7353 0.6525
-3.250 -0.0383 0.02492 0.01870 -0.0608 0.7318 0.6554
-3.000 -0.0310 0.02384 0.01747 -0.0599 0.7282 0.6657
-2.750 -0.0037 0.02373 0.01731 -0.0599 0.7257 0.6681
-2.500 0.0266 0.02384 0.01738 -0.0600 0.7236 0.6699
-2.250 0.0565 0.02396 0.01743 -0.0603 0.7218 0.6719
-2.000 0.0718 0.02422 0.01774 -0.0587 0.7179 0.6749
-1.750 0.0873 0.02417 0.01768 -0.0577 0.7140 0.6794
-1.500 0.1040 0.02345 0.01685 -0.0580 0.7108 0.6860
-1.250 0.1304 0.02345 0.01683 -0.0577 0.7083 0.6878
-1.000 0.1591 0.02342 0.01677 -0.0579 0.7063 0.6897
-0.750 0.1886 0.02336 0.01667 -0.0584 0.7046 0.6916
-0.500 0.2142 0.02342 0.01670 -0.0585 0.7026 0.6940
-0.250 0.2160 0.02402 0.01740 -0.0554 0.6969 0.6979
0.000 0.2351 0.02401 0.01735 -0.0553 0.6934 0.7026
0.250 0.2622 0.02378 0.01706 -0.0561 0.6909 0.7058
0.500 0.2901 0.02371 0.01699 -0.0563 0.6889 0.7075
0.750 0.3192 0.02369 0.01697 -0.0567 0.6873 0.7095
1.000 0.3493 0.02373 0.01699 -0.0573 0.6859 0.7119
1.250 0.3251 0.02552 0.01893 -0.0505 0.6771 0.7157
1.500 0.3467 0.02567 0.01908 -0.0503 0.6738 0.7189
1.750 0.3772 0.02558 0.01895 -0.0516 0.6719 0.7224
2.000 0.4096 0.02544 0.01878 -0.0530 0.6705 0.7252
2.250 0.4401 0.02539 0.01876 -0.0535 0.6692 0.7272
2.500 0.4731 0.02532 0.01871 -0.0544 0.6680 0.7295
2.750 0.5081 0.02525 0.01864 -0.0557 0.6669 0.7322
3.000 0.3809 0.03114 0.02470 -0.0362 0.6452 0.7377
3.250 0.4308 0.03016 0.02371 -0.0393 0.6461 0.7408
3.500 0.4027 0.03310 0.02665 -0.0341 0.6344 0.7446
3.750 0.3965 0.03502 0.02862 -0.0309 0.6270 0.7473
4.000 0.4472 0.03382 0.02747 -0.0333 0.6287 0.7498
4.250 0.4940 0.03277 0.02646 -0.0353 0.6295 0.7529
4.500 0.5404 0.03179 0.02552 -0.0375 0.6299 0.7563
4.750 0.5910 0.03075 0.02451 -0.0406 0.6303 0.7598
5.000 0.5434 0.03481 0.02858 -0.0333 0.6151 0.7643
5.250 0.5833 0.03400 0.02785 -0.0345 0.6147 0.7669
5.500 0.6253 0.03305 0.02697 -0.0358 0.6144 0.7699
5.750 0.6698 0.03208 0.02606 -0.0377 0.6141 0.7732
6.000 0.7199 0.03090 0.02494 -0.0404 0.6139 0.7772
6.250 0.7746 0.02970 0.02378 -0.0440 0.6133 0.7814
6.500 0.6344 0.03858 0.03271 -0.0273 0.5815 0.7870
6.750 0.6211 0.04094 0.03513 -0.0240 0.5690 0.7914
7.000 0.6583 0.04011 0.03437 -0.0248 0.5669 0.7960
7.250 0.7045 0.03867 0.03298 -0.0264 0.5660 0.8009
7.500 0.7518 0.03673 0.03116 -0.0275 0.5657 0.8046
7.750 0.8004 0.03470 0.02923 -0.0287 0.5659 0.8089
8.000 0.8656 0.03160 0.02624 -0.0315 0.5672 0.8139
8.250 1.0629 0.02165 0.01622 -0.0495 0.5651 0.8154
8.500 1.0713 0.02151 0.01614 -0.0464 0.5555 0.8215
8.750 1.1028 0.02046 0.01510 -0.0461 0.5441 0.8261
9.000 1.0858 0.02139 0.01618 -0.0399 0.5333 0.8340
9.250 1.0898 0.02170 0.01656 -0.0367 0.5214 0.8406
9.500 1.0965 0.02194 0.01686 -0.0337 0.5082 0.8477
9.750 1.0966 0.02268 0.01766 -0.0305 0.4917 0.8563
10.000 1.0921 0.02359 0.01865 -0.0266 0.4737 0.8647
10.250 1.0951 0.02431 0.01932 -0.0238 0.4470 0.8740
10.500 1.0929 0.02521 0.02011 -0.0202 0.4135 0.8836
10.750 1.0846 0.02662 0.02132 -0.0164 0.3745 0.8944
11.000 1.0712 0.02855 0.02304 -0.0125 0.3374 0.9072
11.250 1.0552 0.03078 0.02509 -0.0087 0.3022 0.9226
11.500 1.0393 0.03327 0.02741 -0.0054 0.2666 0.9437
11.750 1.0296 0.03626 0.03022 -0.0048 0.2257 0.9899
12.000 1.0187 0.03980 0.03348 -0.0043 0.1841 1.0000
12.250 1.0057 0.04364 0.03697 -0.0037 0.1379 1.0000
12.500 0.9926 0.04757 0.04052 -0.0031 0.0945 1.0000
12.750 0.9878 0.05084 0.04358 -0.0028 0.0761 1.0000
13.000 0.9879 0.05373 0.04639 -0.0027 0.0671 1.0000
13.250 0.9927 0.05619 0.04883 -0.0028 0.0615 1.0000
13.500 0.9965 0.05873 0.05137 -0.0028 0.0578 1.0000
13.750 1.0036 0.06095 0.05360 -0.0029 0.0548 1.0000
14.000 1.0070 0.06349 0.05607 -0.0029 0.0524 1.0000
14.250 1.0170 0.06544 0.05809 -0.0031 0.0501 1.0000
14.500 1.0258 0.06745 0.06010 -0.0031 0.0480 1.0000
14.750 1.0357 0.06927 0.06188 -0.0031 0.0468 1.0000
15.000 1.0485 0.07070 0.06328 -0.0029 0.0455 1.0000
15.250 1.0623 0.07217 0.06482 -0.0029 0.0443 1.0000
15.500 1.0769 0.07352 0.06620 -0.0029 0.0432 1.0000
15.750 1.0920 0.07481 0.06748 -0.0029 0.0420 1.0000
16.000 1.1105 0.07565 0.06827 -0.0028 0.0410 1.0000
16.250 1.1346 0.07592 0.06848 -0.0024 0.0398 1.0000
16.500 1.1469 0.07769 0.07039 -0.0025 0.0390 1.0000
16.750 1.1626 0.07909 0.07188 -0.0025 0.0384 1.0000
17.000 1.1784 0.08052 0.07341 -0.0026 0.0378 1.0000
17.250 1.1941 0.08201 0.07499 -0.0026 0.0372 1.0000
17.500 1.2091 0.08360 0.07667 -0.0028 0.0368 1.0000
17.750 1.2224 0.08540 0.07856 -0.0029 0.0363 1.0000
18.000 1.2356 0.08730 0.08055 -0.0032 0.0360 1.0000
18.250 1.2487 0.08928 0.08264 -0.0034 0.0357 1.0000
18.500 1.2646 0.09115 0.08458 -0.0036 0.0353 1.0000
18.750 1.2814 0.09341 0.08693 -0.0038 0.0349 1.0000
19.000 1.2734 0.09748 0.09124 -0.0047 0.0348 1.0000
19.250 1.2620 0.10203 0.09604 -0.0059 0.0347 1.0000
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