NACA 63-215 AIRFOIL (n63215-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-215 AIRFOIL (n63215-il) Reynolds number: 200,000 Max Cl/Cd: 65.48 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63215-il-200000.txt Download as CSV file: xf-n63215-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-215 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5867 0.13624 0.13250 -0.0181 1.0000 0.0737
-13.750 -0.7195 0.08919 0.08520 -0.0414 1.0000 0.0442
-13.500 -0.7399 0.08185 0.07778 -0.0454 1.0000 0.0436
-13.250 -0.7671 0.07461 0.07042 -0.0496 1.0000 0.0431
-13.000 -0.7941 0.06821 0.06386 -0.0529 1.0000 0.0426
-12.750 -0.8196 0.06266 0.05812 -0.0552 1.0000 0.0421
-12.500 -0.8428 0.05780 0.05306 -0.0563 1.0000 0.0416
-12.250 -0.8641 0.05358 0.04860 -0.0565 1.0000 0.0414
-12.000 -0.8832 0.04979 0.04457 -0.0557 1.0000 0.0411
-11.750 -0.8973 0.04667 0.04121 -0.0540 1.0000 0.0409
-11.500 -0.9068 0.04402 0.03831 -0.0517 1.0000 0.0410
-11.250 -0.9084 0.04147 0.03551 -0.0498 1.0000 0.0413
-11.000 -0.9047 0.03922 0.03301 -0.0481 1.0000 0.0420
-10.750 -0.8978 0.03717 0.03071 -0.0465 1.0000 0.0428
-10.500 -0.8891 0.03533 0.02857 -0.0449 1.0000 0.0437
-10.250 -0.8791 0.03391 0.02685 -0.0432 1.0000 0.0445
-10.000 -0.8609 0.03109 0.02391 -0.0426 1.0000 0.0456
-9.750 -0.8430 0.02954 0.02237 -0.0416 1.0000 0.0467
-9.500 -0.8319 0.02854 0.02134 -0.0396 1.0000 0.0480
-9.250 -0.8323 0.02793 0.02069 -0.0356 1.0000 0.0490
-9.000 -0.8210 0.02714 0.01981 -0.0338 0.9979 0.0507
-8.750 -0.7825 0.02603 0.01844 -0.0366 0.9914 0.0530
-8.500 -0.7463 0.02399 0.01652 -0.0389 0.9866 0.0560
-8.250 -0.7070 0.02288 0.01539 -0.0419 0.9816 0.0597
-8.000 -0.6702 0.02171 0.01414 -0.0443 0.9750 0.0638
-7.750 -0.6324 0.02045 0.01296 -0.0472 0.9698 0.0686
-7.500 -0.5985 0.01966 0.01208 -0.0491 0.9607 0.0739
-7.250 -0.5680 0.01846 0.01097 -0.0507 0.9521 0.0810
-7.000 -0.5401 0.01752 0.01004 -0.0516 0.9421 0.0900
-6.750 -0.5184 0.01670 0.00926 -0.0512 0.9302 0.1033
-6.500 -0.5004 0.01572 0.00845 -0.0502 0.9187 0.1318
-6.250 -0.4876 0.01432 0.00757 -0.0487 0.9078 0.2190
-6.000 -0.4748 0.01312 0.00701 -0.0471 0.8964 0.3441
-5.750 -0.4543 0.01275 0.00690 -0.0460 0.8869 0.4223
-5.500 -0.4305 0.01265 0.00684 -0.0450 0.8786 0.4649
-5.250 -0.4057 0.01266 0.00683 -0.0443 0.8696 0.4936
-5.000 -0.3803 0.01269 0.00680 -0.0435 0.8620 0.5164
-4.750 -0.3545 0.01275 0.00679 -0.0430 0.8534 0.5360
-4.500 -0.3286 0.01283 0.00679 -0.0423 0.8461 0.5539
-4.250 -0.3025 0.01297 0.00693 -0.0417 0.8381 0.5714
-4.000 -0.2765 0.01312 0.00703 -0.0409 0.8306 0.5879
-3.750 -0.2500 0.01326 0.00714 -0.0403 0.8234 0.6017
-3.500 -0.2233 0.01336 0.00724 -0.0397 0.8158 0.6121
-3.250 -0.1964 0.01341 0.00721 -0.0392 0.8096 0.6228
-3.000 -0.1695 0.01351 0.00728 -0.0388 0.8013 0.6343
-2.750 -0.1426 0.01356 0.00730 -0.0382 0.7953 0.6425
-2.500 -0.1150 0.01356 0.00723 -0.0383 0.7877 0.6516
-2.250 -0.0877 0.01354 0.00720 -0.0378 0.7809 0.6577
-2.000 -0.0601 0.01355 0.00715 -0.0377 0.7746 0.6652
-1.750 -0.0325 0.01352 0.00709 -0.0376 0.7672 0.6722
-1.500 -0.0049 0.01352 0.00705 -0.0373 0.7617 0.6786
-1.250 0.0231 0.01351 0.00699 -0.0375 0.7541 0.6867
-1.000 0.0503 0.01350 0.00699 -0.0372 0.7477 0.6922
-0.750 0.0784 0.01351 0.00695 -0.0371 0.7422 0.6995
-0.500 0.1060 0.01351 0.00696 -0.0371 0.7347 0.7059
-0.250 0.1337 0.01350 0.00693 -0.0369 0.7292 0.7121
0.000 0.1621 0.01352 0.00692 -0.0372 0.7225 0.7200
0.250 0.1891 0.01354 0.00698 -0.0368 0.7160 0.7254
0.500 0.2175 0.01355 0.00693 -0.0368 0.7111 0.7327
0.750 0.2448 0.01358 0.00702 -0.0368 0.7035 0.7393
1.000 0.2722 0.01361 0.00706 -0.0366 0.6977 0.7458
1.250 0.3007 0.01364 0.00706 -0.0367 0.6920 0.7538
1.500 0.3271 0.01369 0.00719 -0.0364 0.6849 0.7595
1.750 0.3556 0.01371 0.00718 -0.0364 0.6795 0.7675
2.000 0.3821 0.01378 0.00732 -0.0361 0.6726 0.7740
2.250 0.4094 0.01381 0.00739 -0.0359 0.6660 0.7815
2.500 0.4375 0.01384 0.00740 -0.0358 0.6608 0.7889
2.750 0.4632 0.01392 0.00760 -0.0354 0.6529 0.7961
3.000 0.4914 0.01393 0.00760 -0.0353 0.6471 0.8043
3.250 0.5168 0.01402 0.00778 -0.0348 0.6399 0.8114
3.500 0.5444 0.01403 0.00782 -0.0347 0.6327 0.8201
3.750 0.5697 0.01404 0.00790 -0.0339 0.6250 0.8274
4.000 0.5966 0.01398 0.00785 -0.0335 0.6155 0.8364
4.250 0.6208 0.01395 0.00791 -0.0325 0.6058 0.8441
4.500 0.6478 0.01389 0.00784 -0.0321 0.5972 0.8532
4.750 0.6710 0.01385 0.00791 -0.0310 0.5859 0.8620
5.000 0.6954 0.01377 0.00787 -0.0300 0.5746 0.8713
5.250 0.7193 0.01364 0.00776 -0.0289 0.5609 0.8815
5.500 0.7408 0.01348 0.00765 -0.0273 0.5451 0.8913
5.750 0.7625 0.01337 0.00759 -0.0258 0.5286 0.9025
6.000 0.7838 0.01332 0.00759 -0.0244 0.5127 0.9150
6.250 0.8038 0.01325 0.00760 -0.0226 0.4954 0.9285
6.500 0.8246 0.01321 0.00761 -0.0211 0.4747 0.9436
6.750 0.8499 0.01323 0.00765 -0.0207 0.4478 0.9593
7.000 0.8820 0.01347 0.00782 -0.0220 0.4036 0.9750
7.250 0.9116 0.01420 0.00822 -0.0236 0.3262 1.0000
7.500 0.9192 0.01542 0.00896 -0.0218 0.2464 1.0000
7.750 0.9254 0.01707 0.01008 -0.0201 0.1679 1.0000
8.000 0.9318 0.01869 0.01130 -0.0183 0.1188 1.0000
8.250 0.9392 0.02001 0.01245 -0.0162 0.0974 1.0000
8.500 0.9458 0.02125 0.01358 -0.0140 0.0865 1.0000
8.750 0.9553 0.02238 0.01468 -0.0124 0.0786 1.0000
9.000 0.9642 0.02364 0.01593 -0.0107 0.0731 1.0000
9.250 0.9755 0.02478 0.01708 -0.0095 0.0682 1.0000
9.500 0.9833 0.02632 0.01856 -0.0080 0.0643 1.0000
9.750 0.9974 0.02740 0.01972 -0.0070 0.0607 1.0000
10.000 1.0095 0.02864 0.02093 -0.0060 0.0574 1.0000
10.250 1.0229 0.03017 0.02241 -0.0049 0.0544 1.0000
10.500 1.0388 0.03134 0.02369 -0.0041 0.0521 1.0000
10.750 1.0546 0.03257 0.02494 -0.0033 0.0497 1.0000
11.000 1.0724 0.03390 0.02621 -0.0027 0.0474 1.0000
11.250 1.0924 0.03543 0.02781 -0.0021 0.0453 1.0000
11.500 1.1079 0.03680 0.02932 -0.0014 0.0434 1.0000
11.750 1.1257 0.03826 0.03087 -0.0008 0.0420 1.0000
12.000 1.1435 0.03977 0.03242 -0.0003 0.0408 1.0000
12.250 1.1765 0.04196 0.03457 -0.0008 0.0392 1.0000
12.500 1.1869 0.04418 0.03702 0.0001 0.0385 1.0000
12.750 1.1908 0.04630 0.03940 0.0013 0.0378 1.0000
13.000 1.1939 0.04871 0.04207 0.0023 0.0371 1.0000
13.250 1.1948 0.05118 0.04476 0.0032 0.0364 1.0000
13.500 1.1949 0.05388 0.04766 0.0039 0.0357 1.0000
13.750 1.1929 0.05693 0.05094 0.0044 0.0354 1.0000
14.000 1.1868 0.06047 0.05471 0.0046 0.0352 1.0000
14.250 1.1777 0.06430 0.05877 0.0046 0.0350 1.0000
14.500 1.1647 0.06865 0.06336 0.0041 0.0349 1.0000
14.750 1.1450 0.07399 0.06898 0.0030 0.0350 1.0000
15.000 1.1213 0.08009 0.07536 0.0010 0.0352 1.0000
15.250 1.0911 0.08749 0.08305 -0.0021 0.0355 1.0000
15.500 1.0576 0.09614 0.09197 -0.0066 0.0360 1.0000
15.750 1.0204 0.10641 0.10249 -0.0127 0.0366 1.0000
16.000 0.9816 0.11833 0.11462 -0.0203 0.0373 1.0000
16.250 0.9421 0.13211 0.12855 -0.0293 0.0381 1.0000
16.500 0.9230 0.14214 0.13862 -0.0349 0.0388 1.0000
16.750 0.8337 0.19022 0.18677 -0.0564 0.0649 1.0000
17.000 0.6624 0.18259 0.17971 -0.0523 0.0650 1.0000
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