NACA 64(1)-212 MOD B (n64212mb-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-212 MOD B (n64212mb-il) Reynolds number: 500,000 Max Cl/Cd: 76.46 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64212mb-il-500000-n5.txt Download as CSV file: xf-n64212mb-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-212 MOD B
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8813 0.06298 0.05973 -0.0414 1.0000 0.0133
-13.750 -0.9140 0.05486 0.05135 -0.0464 1.0000 0.0133
-13.500 -0.9352 0.04920 0.04545 -0.0491 1.0000 0.0133
-13.250 -0.9501 0.04481 0.04085 -0.0505 1.0000 0.0134
-13.000 -0.9621 0.04110 0.03693 -0.0509 1.0000 0.0134
-12.750 -0.9693 0.03810 0.03374 -0.0507 1.0000 0.0135
-12.500 -0.9744 0.03549 0.03092 -0.0498 1.0000 0.0135
-12.250 -0.9757 0.03338 0.02864 -0.0485 1.0000 0.0137
-12.000 -0.9760 0.03145 0.02652 -0.0468 1.0000 0.0138
-11.750 -0.9737 0.02991 0.02482 -0.0446 1.0000 0.0139
-11.500 -0.9672 0.02843 0.02316 -0.0426 1.0000 0.0140
-11.250 -0.9558 0.02707 0.02165 -0.0412 1.0000 0.0141
-11.000 -0.9420 0.02587 0.02031 -0.0399 1.0000 0.0142
-10.750 -0.9266 0.02474 0.01903 -0.0387 1.0000 0.0143
-10.500 -0.9111 0.02354 0.01772 -0.0374 1.0000 0.0145
-10.250 -0.8938 0.02261 0.01674 -0.0364 1.0000 0.0148
-10.000 -0.8752 0.02182 0.01591 -0.0353 1.0000 0.0149
-9.750 -0.8561 0.02112 0.01517 -0.0343 1.0000 0.0151
-9.500 -0.8370 0.02045 0.01446 -0.0332 1.0000 0.0154
-9.250 -0.8143 0.01970 0.01365 -0.0328 0.9969 0.0156
-9.000 -0.7834 0.01886 0.01274 -0.0340 0.9850 0.0158
-8.750 -0.7518 0.01807 0.01188 -0.0354 0.9745 0.0161
-8.500 -0.7202 0.01732 0.01106 -0.0366 0.9639 0.0165
-8.250 -0.6899 0.01662 0.01028 -0.0375 0.9527 0.0168
-8.000 -0.6618 0.01601 0.00959 -0.0379 0.9406 0.0170
-7.750 -0.6359 0.01548 0.00898 -0.0377 0.9281 0.0173
-7.500 -0.6124 0.01492 0.00836 -0.0371 0.9154 0.0176
-7.250 -0.5888 0.01443 0.00784 -0.0364 0.9041 0.0180
-7.000 -0.5646 0.01403 0.00738 -0.0358 0.8938 0.0184
-6.750 -0.5401 0.01365 0.00696 -0.0352 0.8835 0.0189
-6.500 -0.5152 0.01328 0.00654 -0.0347 0.8743 0.0195
-6.250 -0.4900 0.01295 0.00615 -0.0342 0.8654 0.0202
-6.000 -0.4644 0.01263 0.00577 -0.0338 0.8570 0.0210
-5.750 -0.4389 0.01227 0.00540 -0.0334 0.8483 0.0220
-5.500 -0.4128 0.01198 0.00508 -0.0330 0.8405 0.0231
-5.250 -0.3865 0.01172 0.00476 -0.0327 0.8315 0.0244
-5.000 -0.3604 0.01143 0.00443 -0.0323 0.8194 0.0259
-4.750 -0.3343 0.01120 0.00414 -0.0319 0.8055 0.0278
-4.500 -0.3078 0.01100 0.00387 -0.0315 0.7925 0.0299
-4.250 -0.2810 0.01076 0.00362 -0.0312 0.7800 0.0328
-4.000 -0.2539 0.01057 0.00338 -0.0310 0.7676 0.0362
-3.750 -0.2269 0.01038 0.00316 -0.0307 0.7548 0.0415
-3.500 -0.1999 0.01017 0.00295 -0.0305 0.7408 0.0508
-3.250 -0.1729 0.00990 0.00274 -0.0303 0.7280 0.0719
-3.000 -0.1464 0.00952 0.00251 -0.0302 0.7139 0.1202
-2.750 -0.1206 0.00896 0.00224 -0.0301 0.6992 0.2098
-2.500 -0.0955 0.00818 0.00193 -0.0301 0.6849 0.3472
-2.250 -0.0694 0.00771 0.00180 -0.0300 0.6694 0.4596
-2.000 -0.0418 0.00760 0.00175 -0.0299 0.6520 0.4992
-1.750 -0.0142 0.00752 0.00171 -0.0297 0.6334 0.5347
-1.500 0.0127 0.00746 0.00174 -0.0294 0.6092 0.5860
-1.250 0.0397 0.00756 0.00175 -0.0291 0.5730 0.6125
-1.000 0.0657 0.00781 0.00174 -0.0286 0.5006 0.6224
-0.750 0.0875 0.00877 0.00194 -0.0279 0.3074 0.6297
-0.250 0.1426 0.00913 0.00204 -0.0277 0.2477 0.6415
0.000 0.1706 0.00927 0.00208 -0.0277 0.2311 0.6478
0.250 0.1985 0.00937 0.00213 -0.0276 0.2187 0.6542
0.500 0.2266 0.00947 0.00218 -0.0276 0.2096 0.6612
0.750 0.2546 0.00959 0.00225 -0.0276 0.2021 0.6674
1.000 0.2826 0.00967 0.00232 -0.0275 0.1957 0.6742
1.250 0.3106 0.00980 0.00239 -0.0275 0.1895 0.6812
1.500 0.3385 0.00990 0.00249 -0.0274 0.1851 0.6878
1.750 0.3665 0.00999 0.00258 -0.0273 0.1816 0.6953
2.000 0.3944 0.01010 0.00268 -0.0273 0.1780 0.7027
2.250 0.4220 0.01022 0.00280 -0.0272 0.1745 0.7107
2.500 0.4496 0.01038 0.00293 -0.0271 0.1712 0.7183
2.750 0.4773 0.01048 0.00307 -0.0270 0.1691 0.7259
3.000 0.5051 0.01060 0.00320 -0.0269 0.1669 0.7339
3.250 0.5325 0.01071 0.00334 -0.0267 0.1643 0.7414
3.500 0.5600 0.01085 0.00349 -0.0266 0.1617 0.7497
3.750 0.5871 0.01100 0.00366 -0.0264 0.1595 0.7577
4.000 0.6140 0.01118 0.00384 -0.0263 0.1573 0.7668
4.250 0.6405 0.01139 0.00406 -0.0260 0.1549 0.7753
4.500 0.6677 0.01153 0.00425 -0.0258 0.1538 0.7844
4.750 0.6945 0.01167 0.00445 -0.0256 0.1525 0.7928
5.000 0.7214 0.01183 0.00465 -0.0254 0.1509 0.8019
5.250 0.7479 0.01198 0.00486 -0.0251 0.1490 0.8109
5.750 0.8003 0.01234 0.00529 -0.0244 0.1454 0.8305
6.000 0.8261 0.01255 0.00554 -0.0241 0.1438 0.8404
6.250 0.8512 0.01279 0.00581 -0.0236 0.1421 0.8513
6.500 0.8755 0.01308 0.00614 -0.0229 0.1402 0.8621
6.750 0.9009 0.01323 0.00638 -0.0224 0.1391 0.8738
7.000 0.9257 0.01339 0.00662 -0.0218 0.1377 0.8867
7.250 0.9498 0.01352 0.00683 -0.0211 0.1355 0.9008
7.500 0.9735 0.01364 0.00701 -0.0202 0.1326 0.9170
7.750 0.9964 0.01379 0.00720 -0.0193 0.1300 0.9360
8.250 1.0524 0.01420 0.00769 -0.0197 0.1244 1.0000
8.500 1.0788 0.01443 0.00796 -0.0196 0.1219 1.0000
8.750 1.1048 0.01467 0.00822 -0.0195 0.1190 1.0000
9.000 1.1302 0.01494 0.00849 -0.0193 0.1159 1.0000
9.250 1.1553 0.01524 0.00881 -0.0190 0.1130 1.0000
9.500 1.1808 0.01549 0.00912 -0.0188 0.1094 1.0000
9.750 1.2057 0.01577 0.00941 -0.0185 0.1047 1.0000
10.000 1.2300 0.01610 0.00975 -0.0182 0.1002 1.0000
10.250 1.2539 0.01645 0.01010 -0.0178 0.0937 1.0000
10.500 1.2770 0.01685 0.01051 -0.0173 0.0870 1.0000
10.750 1.2988 0.01737 0.01099 -0.0167 0.0782 1.0000
11.000 1.3193 0.01799 0.01157 -0.0159 0.0690 1.0000
11.250 1.3384 0.01870 0.01225 -0.0150 0.0607 1.0000
11.500 1.3566 0.01946 0.01300 -0.0140 0.0545 1.0000
11.750 1.3748 0.02016 0.01373 -0.0130 0.0496 1.0000
12.000 1.3916 0.02091 0.01450 -0.0118 0.0459 1.0000
12.250 1.4061 0.02165 0.01528 -0.0102 0.0424 1.0000
12.500 1.4190 0.02245 0.01612 -0.0085 0.0397 1.0000
12.750 1.4315 0.02325 0.01698 -0.0068 0.0372 1.0000
13.000 1.4417 0.02423 0.01799 -0.0050 0.0349 1.0000
13.250 1.4531 0.02512 0.01896 -0.0034 0.0332 1.0000
13.500 1.4628 0.02616 0.02006 -0.0019 0.0315 1.0000
13.750 1.4706 0.02737 0.02133 -0.0003 0.0301 1.0000
14.000 1.4782 0.02862 0.02267 0.0011 0.0290 1.0000
14.250 1.4857 0.02992 0.02407 0.0023 0.0279 1.0000
14.500 1.4914 0.03143 0.02566 0.0035 0.0269 1.0000
14.750 1.4950 0.03317 0.02749 0.0045 0.0260 1.0000
15.000 1.4952 0.03530 0.02970 0.0054 0.0250 1.0000
15.250 1.4975 0.03734 0.03185 0.0060 0.0243 1.0000
15.500 1.4984 0.03962 0.03425 0.0064 0.0237 1.0000
15.750 1.4966 0.04229 0.03704 0.0064 0.0231 1.0000
16.000 1.4920 0.04544 0.04030 0.0061 0.0226 1.0000
16.250 1.4834 0.04924 0.04424 0.0053 0.0221 1.0000
16.500 1.4712 0.05381 0.04896 0.0038 0.0217 1.0000
16.750 1.4525 0.05970 0.05501 0.0013 0.0215 1.0000
17.000 1.4264 0.06752 0.06304 -0.0029 0.0215 1.0000
17.250 1.3834 0.08003 0.07584 -0.0105 0.0218 1.0000
17.500 1.3243 0.09586 0.09196 -0.0197 0.0222 1.0000
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