NACA 64(1)-212 (n64212-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 (n64212-il) Reynolds number: 200,000 Max Cl/Cd: 55.94 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212-il-200000-n5.txt Download as CSV file: xf-n64212-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6501 0.08345 0.07971 -0.0321 1.0000 0.0188
-11.750 -0.6806 0.07231 0.06846 -0.0404 1.0000 0.0185
-11.500 -0.7086 0.06429 0.06029 -0.0461 1.0000 0.0184
-11.250 -0.7312 0.05848 0.05431 -0.0494 1.0000 0.0183
-11.000 -0.7527 0.05359 0.04924 -0.0511 1.0000 0.0183
-10.750 -0.7726 0.04951 0.04495 -0.0511 1.0000 0.0183
-10.500 -0.7923 0.04597 0.04114 -0.0493 1.0000 0.0184
-10.250 -0.8037 0.04250 0.03735 -0.0473 1.0000 0.0186
-10.000 -0.8086 0.03901 0.03343 -0.0454 1.0000 0.0188
-9.750 -0.8063 0.03609 0.03008 -0.0437 1.0000 0.0191
-9.500 -0.7972 0.03380 0.02760 -0.0424 1.0000 0.0196
-9.250 -0.7830 0.03252 0.02625 -0.0415 1.0000 0.0202
-9.000 -0.7682 0.03137 0.02499 -0.0404 1.0000 0.0208
-8.750 -0.7537 0.03000 0.02346 -0.0390 1.0000 0.0215
-8.500 -0.7400 0.02841 0.02166 -0.0374 1.0000 0.0221
-8.250 -0.7267 0.02692 0.01995 -0.0355 1.0000 0.0226
-8.000 -0.6993 0.02522 0.01799 -0.0364 0.9926 0.0233
-7.750 -0.6671 0.02369 0.01621 -0.0379 0.9851 0.0241
-7.500 -0.6359 0.02231 0.01467 -0.0393 0.9767 0.0253
-7.250 -0.6048 0.02118 0.01351 -0.0408 0.9682 0.0265
-7.000 -0.5731 0.02017 0.01243 -0.0422 0.9601 0.0277
-6.750 -0.5424 0.01920 0.01138 -0.0432 0.9508 0.0289
-6.500 -0.5134 0.01833 0.01041 -0.0439 0.9407 0.0303
-6.250 -0.4844 0.01758 0.00954 -0.0445 0.9310 0.0317
-6.000 -0.4588 0.01669 0.00864 -0.0446 0.9201 0.0340
-5.750 -0.4333 0.01613 0.00804 -0.0445 0.9091 0.0367
-5.500 -0.4079 0.01561 0.00742 -0.0443 0.8988 0.0396
-5.250 -0.3834 0.01504 0.00676 -0.0439 0.8887 0.0426
-5.000 -0.3591 0.01456 0.00626 -0.0435 0.8782 0.0477
-4.750 -0.3342 0.01413 0.00577 -0.0431 0.8687 0.0539
-4.500 -0.3094 0.01371 0.00531 -0.0427 0.8593 0.0641
-4.250 -0.2850 0.01318 0.00487 -0.0423 0.8498 0.0878
-4.000 -0.2616 0.01248 0.00442 -0.0420 0.8412 0.1517
-3.500 -0.2186 0.01053 0.00373 -0.0411 0.8232 0.4613
-3.250 -0.1927 0.01035 0.00366 -0.0407 0.8146 0.5157
-3.000 -0.1661 0.01027 0.00360 -0.0403 0.8066 0.5543
-2.750 -0.1401 0.01022 0.00363 -0.0397 0.7986 0.5967
-2.500 -0.1143 0.01026 0.00374 -0.0390 0.7906 0.6348
-2.250 -0.0875 0.01027 0.00373 -0.0386 0.7827 0.6527
-2.000 -0.0596 0.01025 0.00362 -0.0386 0.7748 0.6621
-1.750 -0.0322 0.01023 0.00356 -0.0384 0.7674 0.6696
-1.500 -0.0040 0.01021 0.00346 -0.0384 0.7601 0.6775
-1.250 0.0237 0.01018 0.00341 -0.0383 0.7528 0.6831
-1.000 0.0517 0.01018 0.00335 -0.0383 0.7457 0.6903
-0.750 0.0795 0.01016 0.00330 -0.0383 0.7381 0.6963
-0.500 0.1074 0.01016 0.00327 -0.0382 0.7313 0.7029
-0.250 0.1355 0.01017 0.00326 -0.0383 0.7241 0.7101
0.000 0.1631 0.01018 0.00326 -0.0382 0.7182 0.7169
0.250 0.1913 0.01020 0.00328 -0.0383 0.7110 0.7246
0.500 0.2188 0.01022 0.00330 -0.0381 0.7048 0.7310
0.750 0.2470 0.01025 0.00334 -0.0382 0.6978 0.7390
1.000 0.2744 0.01028 0.00340 -0.0380 0.6915 0.7458
1.250 0.3024 0.01033 0.00346 -0.0381 0.6858 0.7545
1.500 0.3297 0.01037 0.00357 -0.0379 0.6793 0.7618
1.750 0.3577 0.01043 0.00364 -0.0379 0.6738 0.7704
2.000 0.3848 0.01048 0.00377 -0.0377 0.6672 0.7777
2.250 0.4124 0.01054 0.00387 -0.0377 0.6605 0.7865
2.500 0.4392 0.01060 0.00400 -0.0374 0.6525 0.7947
2.750 0.4663 0.01066 0.00411 -0.0371 0.6450 0.8037
3.000 0.4930 0.01072 0.00426 -0.0368 0.6365 0.8127
3.250 0.5188 0.01075 0.00432 -0.0362 0.6210 0.8215
3.500 0.5438 0.01077 0.00431 -0.0354 0.5950 0.8315
3.750 0.5673 0.01082 0.00433 -0.0343 0.5631 0.8409
4.000 0.5910 0.01093 0.00440 -0.0334 0.5284 0.8510
4.500 0.6360 0.01137 0.00468 -0.0311 0.4384 0.8731
4.750 0.6510 0.01219 0.00498 -0.0290 0.3243 0.8859
5.000 0.6640 0.01335 0.00560 -0.0270 0.2096 0.9006
5.250 0.6793 0.01433 0.00620 -0.0253 0.1283 0.9174
5.500 0.6980 0.01510 0.00676 -0.0241 0.0830 0.9364
5.750 0.7228 0.01575 0.00733 -0.0240 0.0604 0.9583
6.000 0.7523 0.01639 0.00794 -0.0250 0.0489 1.0000
6.250 0.7747 0.01704 0.00860 -0.0246 0.0427 1.0000
6.500 0.7971 0.01767 0.00926 -0.0242 0.0384 1.0000
6.750 0.8173 0.01849 0.01007 -0.0234 0.0349 1.0000
7.000 0.8389 0.01914 0.01079 -0.0228 0.0322 1.0000
7.250 0.8595 0.01986 0.01156 -0.0221 0.0299 1.0000
7.500 0.8781 0.02076 0.01248 -0.0212 0.0282 1.0000
7.750 0.8950 0.02185 0.01360 -0.0200 0.0269 1.0000
8.000 0.9140 0.02276 0.01460 -0.0190 0.0259 1.0000
8.250 0.9328 0.02376 0.01567 -0.0180 0.0249 1.0000
8.500 0.9515 0.02482 0.01682 -0.0171 0.0240 1.0000
8.750 0.9705 0.02590 0.01797 -0.0162 0.0232 1.0000
9.000 0.9891 0.02695 0.01906 -0.0153 0.0224 1.0000
9.250 1.0068 0.02810 0.02024 -0.0145 0.0216 1.0000
9.500 1.0251 0.02964 0.02184 -0.0137 0.0208 1.0000
9.750 1.0434 0.03095 0.02335 -0.0128 0.0203 1.0000
10.000 1.0611 0.03251 0.02510 -0.0119 0.0198 1.0000
10.250 1.0771 0.03422 0.02703 -0.0108 0.0194 1.0000
10.500 1.0906 0.03608 0.02910 -0.0095 0.0190 1.0000
10.750 1.1010 0.03804 0.03129 -0.0080 0.0186 1.0000
11.000 1.1086 0.04013 0.03362 -0.0064 0.0183 1.0000
11.250 1.1130 0.04230 0.03602 -0.0047 0.0180 1.0000
11.500 1.1151 0.04447 0.03841 -0.0031 0.0177 1.0000
11.750 1.1150 0.04675 0.04090 -0.0016 0.0175 1.0000
12.000 1.1148 0.04885 0.04314 -0.0005 0.0171 1.0000
12.250 1.1118 0.05144 0.04591 0.0004 0.0169 1.0000
12.500 1.1101 0.05383 0.04841 0.0009 0.0166 1.0000
12.750 1.1049 0.05691 0.05163 0.0011 0.0164 1.0000
13.000 1.0953 0.06072 0.05563 0.0009 0.0163 1.0000
13.250 1.0819 0.06520 0.06031 0.0001 0.0162 1.0000
13.500 1.0650 0.07036 0.06568 -0.0015 0.0161 1.0000
13.750 1.0462 0.07619 0.07173 -0.0038 0.0161 1.0000
14.000 1.0254 0.08281 0.07857 -0.0071 0.0161 1.0000
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