NACA 64-110 AIRFOIL (n64110-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-110 AIRFOIL (n64110-il) Reynolds number: 200,000 Max Cl/Cd: 44.62 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64110-il-200000-n5.txt Download as CSV file: xf-n64110-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-110 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6633 0.08128 0.07780 -0.0177 1.0000 0.0158
-10.250 -0.6849 0.07116 0.06762 -0.0258 1.0000 0.0156
-10.000 -0.7057 0.06467 0.06103 -0.0304 1.0000 0.0152
-9.750 -0.7272 0.05950 0.05574 -0.0324 1.0000 0.0149
-9.500 -0.7465 0.05531 0.05138 -0.0319 1.0000 0.0151
-9.250 -0.7582 0.05071 0.04651 -0.0313 1.0000 0.0153
-9.000 -0.7652 0.04582 0.04127 -0.0303 1.0000 0.0158
-8.750 -0.7662 0.04121 0.03622 -0.0290 1.0000 0.0161
-8.500 -0.7616 0.03703 0.03156 -0.0277 1.0000 0.0163
-8.250 -0.7513 0.03356 0.02759 -0.0264 1.0000 0.0167
-8.000 -0.7372 0.03066 0.02424 -0.0252 1.0000 0.0172
-7.750 -0.7209 0.02813 0.02147 -0.0245 1.0000 0.0179
-7.500 -0.7006 0.02706 0.02029 -0.0240 1.0000 0.0189
-7.250 -0.6798 0.02584 0.01890 -0.0234 1.0000 0.0199
-7.000 -0.6587 0.02429 0.01712 -0.0226 1.0000 0.0209
-6.750 -0.6372 0.02272 0.01533 -0.0217 1.0000 0.0216
-6.500 -0.6157 0.02138 0.01381 -0.0207 1.0000 0.0224
-6.250 -0.5946 0.02029 0.01257 -0.0197 1.0000 0.0232
-6.000 -0.5740 0.01961 0.01175 -0.0185 1.0000 0.0242
-5.750 -0.5499 0.01803 0.01015 -0.0185 0.9950 0.0260
-5.500 -0.5171 0.01700 0.00908 -0.0200 0.9859 0.0274
-5.250 -0.4846 0.01612 0.00814 -0.0215 0.9765 0.0291
-5.000 -0.4523 0.01534 0.00726 -0.0228 0.9669 0.0313
-4.750 -0.4201 0.01473 0.00655 -0.0240 0.9572 0.0337
-4.500 -0.3893 0.01396 0.00577 -0.0251 0.9471 0.0390
-4.250 -0.3586 0.01349 0.00521 -0.0259 0.9367 0.0443
-4.000 -0.3303 0.01298 0.00467 -0.0262 0.9253 0.0534
-3.750 -0.3030 0.01248 0.00423 -0.0263 0.9140 0.0748
-3.500 -0.2785 0.01163 0.00376 -0.0263 0.9029 0.1618
-3.250 -0.2588 0.01018 0.00329 -0.0258 0.8915 0.3902
-3.000 -0.2355 0.00970 0.00319 -0.0250 0.8803 0.5108
-2.750 -0.2100 0.00953 0.00312 -0.0243 0.8699 0.5622
-2.500 -0.1858 0.00939 0.00318 -0.0233 0.8600 0.6281
-2.250 -0.1618 0.00937 0.00330 -0.0220 0.8502 0.6785
-2.000 -0.1357 0.00936 0.00325 -0.0214 0.8401 0.6979
-1.750 -0.1088 0.00933 0.00316 -0.0210 0.8310 0.7085
-1.500 -0.0816 0.00931 0.00306 -0.0208 0.8217 0.7185
-1.250 -0.0546 0.00927 0.00300 -0.0205 0.8122 0.7261
-1.000 -0.0273 0.00926 0.00292 -0.0203 0.8035 0.7347
-0.750 -0.0002 0.00924 0.00288 -0.0200 0.7941 0.7432
-0.500 0.0271 0.00923 0.00284 -0.0198 0.7856 0.7517
-0.250 0.0544 0.00923 0.00281 -0.0196 0.7771 0.7606
0.000 0.0815 0.00923 0.00282 -0.0194 0.7679 0.7690
0.250 0.1087 0.00924 0.00281 -0.0191 0.7598 0.7786
0.500 0.1358 0.00925 0.00285 -0.0189 0.7511 0.7877
0.750 0.1629 0.00927 0.00289 -0.0186 0.7432 0.7966
1.000 0.1901 0.00930 0.00293 -0.0184 0.7348 0.8065
1.250 0.2168 0.00932 0.00301 -0.0181 0.7265 0.8159
1.500 0.2436 0.00936 0.00308 -0.0177 0.7190 0.8257
1.750 0.2706 0.00940 0.00318 -0.0175 0.7107 0.8360
2.000 0.2969 0.00944 0.00327 -0.0170 0.7021 0.8460
2.250 0.3230 0.00948 0.00337 -0.0164 0.6911 0.8563
2.500 0.3490 0.00952 0.00346 -0.0159 0.6782 0.8672
2.750 0.3730 0.00954 0.00341 -0.0147 0.6456 0.8789
3.000 0.3956 0.00962 0.00334 -0.0132 0.5896 0.8907
3.250 0.4197 0.00977 0.00338 -0.0122 0.5440 0.9030
3.500 0.4444 0.00996 0.00349 -0.0115 0.4954 0.9163
3.750 0.4645 0.01073 0.00364 -0.0103 0.3456 0.9314
4.000 0.4844 0.01213 0.00424 -0.0098 0.1645 0.9484
4.250 0.5121 0.01314 0.00481 -0.0107 0.0760 0.9647
4.500 0.5446 0.01380 0.00536 -0.0122 0.0511 0.9830
4.750 0.5734 0.01432 0.00590 -0.0129 0.0422 1.0000
5.000 0.5958 0.01503 0.00661 -0.0123 0.0363 1.0000
5.250 0.6196 0.01559 0.00726 -0.0118 0.0337 1.0000
5.500 0.6428 0.01626 0.00799 -0.0113 0.0311 1.0000
5.750 0.6656 0.01700 0.00876 -0.0108 0.0288 1.0000
6.000 0.6862 0.01814 0.00989 -0.0100 0.0263 1.0000
6.250 0.7095 0.01893 0.01078 -0.0095 0.0250 1.0000
6.500 0.7325 0.01989 0.01183 -0.0089 0.0239 1.0000
6.750 0.7556 0.02098 0.01301 -0.0083 0.0229 1.0000
7.000 0.7790 0.02217 0.01431 -0.0077 0.0220 1.0000
7.250 0.8023 0.02348 0.01574 -0.0072 0.0212 1.0000
7.500 0.8254 0.02483 0.01726 -0.0067 0.0205 1.0000
7.750 0.8476 0.02602 0.01855 -0.0063 0.0195 1.0000
8.000 0.8679 0.02800 0.02064 -0.0058 0.0185 1.0000
8.250 0.8880 0.02990 0.02284 -0.0050 0.0179 1.0000
8.500 0.9064 0.03211 0.02542 -0.0040 0.0175 1.0000
8.750 0.9217 0.03479 0.02851 -0.0028 0.0170 1.0000
9.000 0.9329 0.03793 0.03208 -0.0014 0.0166 1.0000
9.250 0.9410 0.04110 0.03569 0.0002 0.0159 1.0000
9.500 0.9458 0.04426 0.03920 0.0018 0.0153 1.0000
9.750 0.9522 0.04636 0.04151 0.0030 0.0145 1.0000
10.000 0.9529 0.04901 0.04438 0.0045 0.0142 1.0000
10.250 0.9439 0.05223 0.04784 0.0066 0.0140 1.0000
10.500 0.9268 0.05593 0.05177 0.0085 0.0140 1.0000
10.750 0.9116 0.05955 0.05556 0.0089 0.0139 1.0000
11.000 0.8885 0.06486 0.06107 0.0076 0.0139 1.0000
11.250 0.8497 0.07416 0.07063 0.0028 0.0142 1.0000
11.500 0.8005 0.09020 0.08684 -0.0085 0.0148 1.0000
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