NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(2)-215 (naca662215-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.58 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca662215-il-1000000.txt Download as CSV file: xf-naca662215-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.3841 0.16400 0.16234 -0.0212 0.9226 0.0136
-17.500 -0.3790 0.16135 0.15966 -0.0230 0.9189 0.0141
-15.750 -0.8671 0.06114 0.05857 -0.0799 1.0000 0.0131
-15.250 -0.8620 0.05645 0.05382 -0.0819 1.0000 0.0133
-15.000 -0.8579 0.05460 0.05194 -0.0824 1.0000 0.0134
-14.750 -0.8762 0.05030 0.04749 -0.0828 1.0000 0.0135
-14.500 -0.9045 0.04520 0.04214 -0.0820 1.0000 0.0135
-14.250 -0.9011 0.04286 0.03971 -0.0828 0.9819 0.0136
-13.750 -0.8699 0.03763 0.03414 -0.0896 0.9616 0.0140
-13.500 -0.8649 0.03442 0.03064 -0.0910 0.9460 0.0142
-13.250 -0.8624 0.03264 0.02863 -0.0897 0.9296 0.0144
-13.000 -0.8633 0.03080 0.02657 -0.0873 0.9162 0.0146
-12.750 -0.8591 0.02960 0.02520 -0.0852 0.9056 0.0149
-12.500 -0.8546 0.02815 0.02354 -0.0830 0.8967 0.0151
-12.250 -0.8473 0.02676 0.02197 -0.0811 0.8887 0.0152
-12.000 -0.8379 0.02594 0.02100 -0.0791 0.8815 0.0155
-11.750 -0.8277 0.02538 0.02033 -0.0772 0.8749 0.0157
-11.500 -0.8144 0.02351 0.01822 -0.0760 0.8698 0.0159
-11.250 -0.7983 0.02218 0.01680 -0.0750 0.8652 0.0164
-11.000 -0.7819 0.02139 0.01595 -0.0739 0.8604 0.0166
-10.750 -0.7665 0.02092 0.01543 -0.0726 0.8555 0.0169
-10.500 -0.7504 0.02042 0.01484 -0.0713 0.8508 0.0172
-10.250 -0.7318 0.01973 0.01409 -0.0704 0.8472 0.0175
-10.000 -0.7132 0.01916 0.01346 -0.0694 0.8433 0.0179
-9.750 -0.6936 0.01853 0.01276 -0.0685 0.8396 0.0182
-9.500 -0.6740 0.01797 0.01210 -0.0676 0.8359 0.0187
-9.250 -0.6539 0.01744 0.01151 -0.0667 0.8327 0.0190
-9.000 -0.6338 0.01693 0.01096 -0.0659 0.8295 0.0193
-8.750 -0.6144 0.01666 0.01062 -0.0648 0.8260 0.0195
-8.500 -0.5962 0.01546 0.00937 -0.0637 0.8230 0.0204
-8.250 -0.5780 0.01502 0.00889 -0.0625 0.8196 0.0209
-8.000 -0.5594 0.01458 0.00844 -0.0613 0.8169 0.0213
-7.750 -0.5406 0.01419 0.00803 -0.0601 0.8142 0.0218
-7.500 -0.5223 0.01381 0.00762 -0.0587 0.8113 0.0224
-7.250 -0.5045 0.01345 0.00722 -0.0572 0.8086 0.0230
-7.000 -0.4864 0.01317 0.00689 -0.0557 0.8060 0.0235
-6.750 -0.4668 0.01295 0.00662 -0.0545 0.8032 0.0240
-6.500 -0.4501 0.01243 0.00607 -0.0528 0.8011 0.0247
-6.250 -0.4322 0.01196 0.00559 -0.0513 0.7989 0.0258
-6.000 -0.4104 0.01168 0.00531 -0.0505 0.7967 0.0269
-5.750 -0.3877 0.01144 0.00506 -0.0498 0.7946 0.0281
-5.500 -0.3648 0.01121 0.00479 -0.0492 0.7926 0.0290
-5.250 -0.3409 0.01103 0.00459 -0.0487 0.7906 0.0297
-5.000 -0.3206 0.01063 0.00414 -0.0476 0.7884 0.0317
-4.750 -0.2971 0.01040 0.00391 -0.0471 0.7865 0.0334
-4.500 -0.2727 0.01020 0.00370 -0.0467 0.7848 0.0354
-4.250 -0.2477 0.01002 0.00352 -0.0464 0.7830 0.0370
-4.000 -0.2239 0.00977 0.00328 -0.0459 0.7813 0.0414
-3.750 -0.1989 0.00958 0.00310 -0.0456 0.7796 0.0469
-3.500 -0.1792 0.00905 0.00284 -0.0445 0.7778 0.1088
-3.250 -0.1675 0.00800 0.00245 -0.0422 0.7760 0.2792
-3.000 -0.1544 0.00696 0.00208 -0.0402 0.7742 0.4543
-2.750 -0.1395 0.00605 0.00184 -0.0383 0.7722 0.6366
-2.500 -0.1125 0.00599 0.00189 -0.0383 0.7710 0.6772
-2.250 -0.0842 0.00601 0.00192 -0.0385 0.7698 0.6980
-2.000 -0.0559 0.00605 0.00198 -0.0387 0.7685 0.7115
-1.750 -0.0273 0.00609 0.00204 -0.0390 0.7671 0.7216
-1.500 0.0012 0.00616 0.00211 -0.0392 0.7656 0.7321
-1.250 0.0300 0.00624 0.00221 -0.0395 0.7642 0.7398
-1.000 0.0590 0.00632 0.00226 -0.0399 0.7629 0.7449
-0.750 0.0878 0.00634 0.00231 -0.0402 0.7617 0.7506
-0.500 0.1169 0.00642 0.00240 -0.0405 0.7605 0.7556
-0.250 0.1461 0.00648 0.00244 -0.0410 0.7593 0.7587
0.000 0.1754 0.00654 0.00248 -0.0415 0.7580 0.7608
0.250 0.2045 0.00654 0.00247 -0.0420 0.7558 0.7624
0.500 0.2331 0.00648 0.00244 -0.0423 0.7533 0.7637
0.750 0.2620 0.00644 0.00241 -0.0427 0.7504 0.7649
1.000 0.2911 0.00642 0.00241 -0.0431 0.7480 0.7661
1.250 0.3203 0.00640 0.00239 -0.0436 0.7454 0.7673
1.500 0.3490 0.00638 0.00235 -0.0439 0.7397 0.7686
1.750 0.3771 0.00631 0.00230 -0.0440 0.7340 0.7700
2.000 0.4057 0.00627 0.00225 -0.0443 0.7290 0.7715
2.250 0.4339 0.00625 0.00223 -0.0445 0.7225 0.7730
2.500 0.4615 0.00619 0.00217 -0.0446 0.7130 0.7744
2.750 0.4891 0.00617 0.00215 -0.0447 0.7037 0.7757
3.000 0.5166 0.00617 0.00214 -0.0447 0.6929 0.7768
3.250 0.5428 0.00614 0.00211 -0.0445 0.6730 0.7786
3.500 0.5678 0.00620 0.00212 -0.0441 0.6457 0.7802
3.750 0.5778 0.00685 0.00232 -0.0407 0.5372 0.7821
4.000 0.5824 0.00781 0.00280 -0.0366 0.4239 0.7843
4.250 0.5852 0.00879 0.00326 -0.0322 0.3107 0.7866
4.500 0.5883 0.00968 0.00371 -0.0279 0.2110 0.7890
4.750 0.5879 0.01050 0.00412 -0.0229 0.1233 0.7914
5.000 0.5901 0.01128 0.00458 -0.0185 0.0549 0.7940
5.250 0.6056 0.01167 0.00492 -0.0165 0.0406 0.7966
5.500 0.6237 0.01200 0.00524 -0.0150 0.0365 0.7989
5.750 0.6416 0.01236 0.00561 -0.0134 0.0334 0.8013
6.000 0.6615 0.01264 0.00592 -0.0123 0.0320 0.8037
6.250 0.6804 0.01298 0.00627 -0.0111 0.0302 0.8061
6.500 0.6974 0.01343 0.00672 -0.0095 0.0280 0.8084
6.750 0.7149 0.01383 0.00716 -0.0081 0.0268 0.8112
7.000 0.7342 0.01414 0.00752 -0.0070 0.0258 0.8139
7.250 0.7527 0.01452 0.00793 -0.0058 0.0246 0.8168
7.500 0.7706 0.01495 0.00837 -0.0045 0.0236 0.8197
7.750 0.7844 0.01560 0.00905 -0.0027 0.0224 0.8229
8.000 0.8001 0.01618 0.00967 -0.0011 0.0216 0.8259
8.250 0.8182 0.01659 0.01014 0.0001 0.0211 0.8293
8.500 0.8364 0.01701 0.01060 0.0012 0.0203 0.8328
8.750 0.8530 0.01755 0.01118 0.0025 0.0197 0.8366
9.000 0.8714 0.01800 0.01164 0.0034 0.0191 0.8402
9.250 0.8875 0.01856 0.01223 0.0047 0.0185 0.8443
9.500 0.8964 0.01958 0.01332 0.0070 0.0178 0.8489
9.750 0.9107 0.02034 0.01414 0.0085 0.0175 0.8533
10.000 0.9283 0.02088 0.01473 0.0095 0.0171 0.8576
10.250 0.9435 0.02154 0.01547 0.0108 0.0169 0.8625
10.500 0.9599 0.02213 0.01613 0.0119 0.0164 0.8677
10.750 0.9753 0.02288 0.01693 0.0131 0.0161 0.8729
11.000 0.9898 0.02360 0.01772 0.0144 0.0159 0.8788
11.250 1.0055 0.02422 0.01840 0.0155 0.0154 0.8854
11.500 1.0194 0.02503 0.01929 0.0168 0.0152 0.8920
11.750 1.0329 0.02585 0.02017 0.0181 0.0150 0.8999
12.000 1.0457 0.02675 0.02115 0.0195 0.0148 0.9082
12.250 1.0579 0.02767 0.02212 0.0208 0.0145 0.9181
12.500 1.0684 0.02934 0.02392 0.0225 0.0141 0.9278
12.750 1.0802 0.03032 0.02504 0.0239 0.0139 0.9428
13.000 1.0986 0.03136 0.02623 0.0237 0.0138 0.9635
13.250 1.1193 0.03256 0.02755 0.0227 0.0135 1.0000
13.500 1.1313 0.03390 0.02898 0.0235 0.0135 1.0000
13.750 1.1419 0.03518 0.03035 0.0244 0.0132 1.0000
14.000 1.1514 0.03663 0.03190 0.0254 0.0130 1.0000
14.250 1.1594 0.03824 0.03362 0.0264 0.0129 1.0000
14.500 1.1661 0.03992 0.03541 0.0273 0.0126 1.0000
14.750 1.1719 0.04167 0.03725 0.0282 0.0125 1.0000
15.000 1.1762 0.04357 0.03926 0.0291 0.0124 1.0000
15.250 1.1783 0.04579 0.04160 0.0300 0.0122 1.0000
15.500 1.1808 0.04791 0.04382 0.0306 0.0121 1.0000
15.750 1.1803 0.05043 0.04646 0.0312 0.0120 1.0000
16.000 1.1787 0.05316 0.04931 0.0316 0.0119 1.0000
16.250 1.1763 0.05606 0.05233 0.0318 0.0118 1.0000
16.500 1.1720 0.05932 0.05570 0.0318 0.0117 1.0000
16.750 1.1683 0.06259 0.05909 0.0315 0.0117 1.0000
17.000 1.1578 0.06698 0.06363 0.0308 0.0116 1.0000
17.250 1.1533 0.07071 0.06746 0.0297 0.0115 1.0000
17.500 1.1335 0.07698 0.07394 0.0279 0.0116 1.0000
17.750 1.1230 0.08212 0.07920 0.0257 0.0115 1.0000
18.000 1.1086 0.08823 0.08545 0.0229 0.0114 1.0000
18.250 1.0782 0.09768 0.09514 0.0180 0.0115 1.0000
18.500 1.0692 0.10352 0.10106 0.0146 0.0114 1.0000
18.750 1.0329 0.11545 0.11323 0.0074 0.0114 1.0000
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