NACA 64(1)-112 (naca641112-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64(1)-112 (naca641112-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.63 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca641112-il-1000000-n5.txt Download as CSV file: xf-naca641112-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(1)-112
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.1281 0.08548 0.08302 -0.0178 1.0000 0.0070
-17.250 -1.1591 0.07526 0.07261 -0.0242 1.0000 0.0070
-17.000 -1.1801 0.06775 0.06494 -0.0286 1.0000 0.0070
-16.750 -1.1947 0.06183 0.05888 -0.0319 1.0000 0.0070
-16.500 -1.2057 0.05689 0.05382 -0.0344 1.0000 0.0071
-16.250 -1.2161 0.05232 0.04912 -0.0364 1.0000 0.0071
-16.000 -1.2210 0.04870 0.04538 -0.0378 1.0000 0.0072
-15.750 -1.2202 0.04592 0.04252 -0.0387 1.0000 0.0073
-15.500 -1.2239 0.04274 0.03922 -0.0395 1.0000 0.0073
-15.250 -1.2236 0.04015 0.03653 -0.0399 1.0000 0.0075
-15.000 -1.2233 0.03765 0.03391 -0.0401 1.0000 0.0075
-14.750 -1.2199 0.03558 0.03175 -0.0400 1.0000 0.0076
-14.500 -1.2166 0.03360 0.02966 -0.0397 1.0000 0.0077
-14.250 -1.2124 0.03177 0.02773 -0.0392 1.0000 0.0078
-14.000 -1.2058 0.03024 0.02611 -0.0386 1.0000 0.0080
-13.750 -1.2005 0.02865 0.02442 -0.0377 1.0000 0.0081
-13.500 -1.1925 0.02736 0.02304 -0.0367 1.0000 0.0082
-13.250 -1.1830 0.02627 0.02186 -0.0356 1.0000 0.0084
-13.000 -1.1737 0.02520 0.02070 -0.0344 1.0000 0.0085
-12.750 -1.1651 0.02415 0.01956 -0.0328 1.0000 0.0086
-12.500 -1.1543 0.02334 0.01866 -0.0312 1.0000 0.0087
-12.250 -1.1443 0.02254 0.01778 -0.0292 1.0000 0.0088
-12.000 -1.1323 0.02173 0.01688 -0.0275 1.0000 0.0090
-11.750 -1.1197 0.02067 0.01575 -0.0260 1.0000 0.0092
-11.500 -1.1030 0.01989 0.01490 -0.0250 1.0000 0.0095
-11.250 -1.0844 0.01921 0.01417 -0.0241 1.0000 0.0097
-11.000 -1.0644 0.01863 0.01355 -0.0234 1.0000 0.0099
-10.500 -1.0231 0.01746 0.01227 -0.0220 1.0000 0.0103
-10.250 -1.0014 0.01694 0.01170 -0.0214 1.0000 0.0105
-10.000 -0.9746 0.01637 0.01108 -0.0219 0.9800 0.0108
-9.750 -0.9413 0.01581 0.01045 -0.0238 0.9574 0.0112
-9.500 -0.9164 0.01537 0.00991 -0.0236 0.9361 0.0114
-9.250 -0.8948 0.01495 0.00937 -0.0228 0.9180 0.0116
-9.000 -0.8727 0.01455 0.00888 -0.0220 0.9026 0.0118
-8.500 -0.8287 0.01353 0.00768 -0.0205 0.8760 0.0125
-8.250 -0.8049 0.01315 0.00724 -0.0200 0.8648 0.0129
-8.000 -0.7805 0.01282 0.00685 -0.0196 0.8541 0.0134
-7.750 -0.7557 0.01251 0.00648 -0.0193 0.8436 0.0138
-7.500 -0.7306 0.01219 0.00609 -0.0190 0.8336 0.0142
-7.250 -0.7053 0.01188 0.00572 -0.0187 0.8242 0.0146
-7.000 -0.6796 0.01160 0.00537 -0.0185 0.8145 0.0150
-6.750 -0.6536 0.01133 0.00504 -0.0184 0.8056 0.0154
-6.500 -0.6279 0.01102 0.00467 -0.0181 0.7968 0.0162
-6.250 -0.6015 0.01074 0.00437 -0.0180 0.7882 0.0173
-6.000 -0.5750 0.01051 0.00410 -0.0180 0.7802 0.0183
-5.750 -0.5481 0.01030 0.00385 -0.0179 0.7715 0.0195
-5.500 -0.5212 0.01009 0.00360 -0.0179 0.7633 0.0210
-5.250 -0.4943 0.00987 0.00336 -0.0178 0.7548 0.0233
-5.000 -0.4670 0.00969 0.00315 -0.0179 0.7473 0.0251
-4.750 -0.4396 0.00953 0.00295 -0.0179 0.7394 0.0268
-4.500 -0.4123 0.00933 0.00275 -0.0179 0.7323 0.0302
-4.250 -0.3847 0.00917 0.00257 -0.0180 0.7245 0.0332
-4.000 -0.3571 0.00901 0.00239 -0.0180 0.7172 0.0383
-3.750 -0.3295 0.00883 0.00222 -0.0181 0.7091 0.0469
-3.250 -0.2752 0.00827 0.00186 -0.0182 0.6942 0.1049
-3.000 -0.2485 0.00790 0.00166 -0.0183 0.6877 0.1585
-2.750 -0.2219 0.00743 0.00145 -0.0184 0.6807 0.2321
-2.500 -0.1954 0.00698 0.00125 -0.0185 0.6742 0.3119
-2.250 -0.1689 0.00647 0.00107 -0.0187 0.6677 0.4050
-2.000 -0.1416 0.00619 0.00099 -0.0188 0.6611 0.4710
-1.750 -0.1135 0.00605 0.00095 -0.0189 0.6549 0.5075
-1.500 -0.0854 0.00592 0.00092 -0.0191 0.6479 0.5445
-1.250 -0.0571 0.00585 0.00091 -0.0192 0.6416 0.5714
-1.000 -0.0284 0.00582 0.00089 -0.0194 0.6352 0.5833
-0.500 0.0292 0.00580 0.00087 -0.0198 0.6238 0.5981
-0.250 0.0580 0.00580 0.00086 -0.0200 0.6180 0.6046
0.000 0.0868 0.00581 0.00086 -0.0202 0.6127 0.6110
0.250 0.1157 0.00581 0.00087 -0.0204 0.6070 0.6165
0.500 0.1444 0.00583 0.00088 -0.0206 0.6004 0.6222
0.750 0.1732 0.00584 0.00090 -0.0208 0.5934 0.6282
1.000 0.2019 0.00587 0.00092 -0.0210 0.5859 0.6338
1.250 0.2306 0.00588 0.00096 -0.0212 0.5790 0.6402
1.750 0.2874 0.00600 0.00103 -0.0214 0.5473 0.6536
2.000 0.3148 0.00617 0.00107 -0.0215 0.5099 0.6606
2.500 0.3696 0.00656 0.00123 -0.0215 0.4315 0.6742
2.750 0.3947 0.00708 0.00143 -0.0213 0.3443 0.6807
3.000 0.4201 0.00759 0.00167 -0.0212 0.2697 0.6880
3.250 0.4450 0.00815 0.00194 -0.0210 0.1913 0.6947
3.500 0.4707 0.00858 0.00219 -0.0209 0.1366 0.7024
3.750 0.4965 0.00898 0.00242 -0.0208 0.0922 0.7099
4.000 0.5225 0.00934 0.00266 -0.0207 0.0596 0.7182
4.250 0.5491 0.00961 0.00288 -0.0206 0.0428 0.7258
4.500 0.5760 0.00983 0.00309 -0.0205 0.0349 0.7339
4.750 0.6029 0.01003 0.00329 -0.0205 0.0311 0.7412
5.000 0.6297 0.01024 0.00352 -0.0204 0.0275 0.7493
5.250 0.6566 0.01042 0.00374 -0.0204 0.0258 0.7568
5.500 0.6832 0.01064 0.00397 -0.0203 0.0236 0.7656
5.750 0.7093 0.01089 0.00425 -0.0201 0.0211 0.7740
6.000 0.7359 0.01110 0.00450 -0.0200 0.0200 0.7829
6.250 0.7619 0.01133 0.00477 -0.0198 0.0184 0.7914
6.500 0.7876 0.01161 0.00506 -0.0196 0.0169 0.8003
6.750 0.8129 0.01190 0.00540 -0.0193 0.0159 0.8098
7.000 0.8384 0.01217 0.00573 -0.0190 0.0152 0.8192
7.250 0.8635 0.01246 0.00607 -0.0187 0.0145 0.8295
7.500 0.8881 0.01276 0.00643 -0.0183 0.0138 0.8398
7.750 0.9122 0.01310 0.00680 -0.0179 0.0131 0.8506
8.000 0.9354 0.01352 0.00729 -0.0173 0.0125 0.8621
8.250 0.9583 0.01391 0.00776 -0.0166 0.0122 0.8748
8.500 0.9809 0.01427 0.00820 -0.0158 0.0120 0.8886
8.750 1.0025 0.01465 0.00868 -0.0149 0.0118 0.9043
9.000 1.0231 0.01504 0.00915 -0.0138 0.0115 0.9223
9.250 1.0428 0.01542 0.00964 -0.0125 0.0113 0.9455
9.500 1.0701 0.01591 0.01022 -0.0130 0.0111 1.0000
9.750 1.0918 0.01645 0.01079 -0.0124 0.0108 1.0000
10.000 1.1135 0.01693 0.01131 -0.0117 0.0106 1.0000
10.250 1.1345 0.01745 0.01186 -0.0110 0.0103 1.0000
10.500 1.1545 0.01802 0.01248 -0.0102 0.0101 1.0000
10.750 1.1731 0.01867 0.01317 -0.0091 0.0099 1.0000
11.000 1.1900 0.01939 0.01395 -0.0079 0.0097 1.0000
11.250 1.2039 0.02021 0.01483 -0.0063 0.0095 1.0000
11.500 1.2122 0.02120 0.01590 -0.0038 0.0093 1.0000
11.750 1.2237 0.02197 0.01675 -0.0019 0.0092 1.0000
12.000 1.2356 0.02277 0.01762 -0.0002 0.0091 1.0000
12.250 1.2469 0.02366 0.01858 0.0014 0.0090 1.0000
12.500 1.2588 0.02453 0.01954 0.0028 0.0089 1.0000
12.750 1.2686 0.02560 0.02070 0.0043 0.0088 1.0000
13.000 1.2795 0.02662 0.02180 0.0055 0.0086 1.0000
13.250 1.2898 0.02772 0.02298 0.0066 0.0085 1.0000
13.500 1.2987 0.02899 0.02433 0.0076 0.0084 1.0000
13.750 1.3066 0.03039 0.02581 0.0086 0.0082 1.0000
14.000 1.3136 0.03192 0.02743 0.0095 0.0081 1.0000
14.250 1.3197 0.03358 0.02919 0.0102 0.0080 1.0000
14.500 1.3251 0.03536 0.03106 0.0108 0.0079 1.0000
14.750 1.3288 0.03739 0.03319 0.0113 0.0078 1.0000
15.000 1.3346 0.03924 0.03513 0.0115 0.0077 1.0000
15.250 1.3378 0.04146 0.03744 0.0116 0.0076 1.0000
15.500 1.3384 0.04403 0.04012 0.0116 0.0075 1.0000
15.750 1.3386 0.04675 0.04293 0.0112 0.0074 1.0000
16.000 1.3385 0.04961 0.04589 0.0107 0.0074 1.0000
16.250 1.3357 0.05292 0.04930 0.0099 0.0073 1.0000
16.500 1.3312 0.05660 0.05309 0.0088 0.0072 1.0000
16.750 1.3286 0.06023 0.05681 0.0074 0.0071 1.0000
17.000 1.3180 0.06518 0.06188 0.0053 0.0070 1.0000
17.250 1.3053 0.07076 0.06761 0.0027 0.0070 1.0000
17.500 1.2892 0.07728 0.07427 -0.0007 0.0069 1.0000
17.750 1.2709 0.08460 0.08174 -0.0048 0.0069 1.0000
18.000 1.2476 0.09344 0.09075 -0.0100 0.0068 1.0000
18.250 1.2262 0.10241 0.09988 -0.0154 0.0069 1.0000
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