NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16-015 (naca16015-il) Reynolds number: 500,000 Max Cl/Cd: 44.57 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16015-il-500000.txt Download as CSV file: xf-naca16015-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.9018 0.07669 0.07344 -0.0717 1.0000 0.0147
-15.750 -0.9304 0.07065 0.06723 -0.0724 1.0000 0.0147
-15.500 -0.9568 0.06564 0.06205 -0.0718 1.0000 0.0147
-15.250 -0.9815 0.06135 0.05758 -0.0702 1.0000 0.0147
-14.750 -1.0350 0.05335 0.04918 -0.0641 1.0000 0.0148
-14.500 -1.0581 0.04999 0.04562 -0.0602 1.0000 0.0149
-14.250 -1.0762 0.04722 0.04268 -0.0561 1.0000 0.0151
-14.000 -1.0881 0.04518 0.04052 -0.0521 1.0000 0.0153
-13.750 -1.0960 0.04363 0.03888 -0.0482 1.0000 0.0154
-13.500 -1.1030 0.04223 0.03738 -0.0441 1.0000 0.0156
-13.250 -1.1083 0.04109 0.03617 -0.0401 1.0000 0.0158
-13.000 -1.1111 0.03986 0.03483 -0.0365 0.9998 0.0161
-12.750 -1.1022 0.03852 0.03335 -0.0351 0.9985 0.0165
-12.500 -1.0919 0.03729 0.03199 -0.0339 0.9971 0.0170
-12.250 -1.0808 0.03587 0.03039 -0.0326 0.9958 0.0176
-12.000 -1.0675 0.03452 0.02882 -0.0315 0.9946 0.0182
-11.750 -1.0554 0.03350 0.02758 -0.0299 0.9928 0.0186
-11.500 -1.0406 0.03111 0.02501 -0.0288 0.9915 0.0193
-11.250 -1.0241 0.03019 0.02405 -0.0279 0.9898 0.0199
-11.000 -1.0061 0.02946 0.02325 -0.0272 0.9881 0.0206
-10.750 -0.9855 0.02866 0.02235 -0.0268 0.9867 0.0214
-10.500 -0.9624 0.02787 0.02144 -0.0269 0.9855 0.0223
-10.250 -0.9389 0.02735 0.02077 -0.0270 0.9845 0.0232
-10.000 -0.9120 0.02579 0.01913 -0.0278 0.9841 0.0246
-9.750 -0.8949 0.02519 0.01852 -0.0265 0.9818 0.0256
-9.500 -0.8782 0.02463 0.01791 -0.0250 0.9789 0.0266
-9.250 -0.8553 0.02403 0.01723 -0.0247 0.9770 0.0279
-9.000 -0.8303 0.02358 0.01669 -0.0248 0.9754 0.0290
-8.750 -0.8056 0.02237 0.01543 -0.0250 0.9745 0.0309
-8.500 -0.7806 0.02180 0.01486 -0.0253 0.9735 0.0325
-8.250 -0.7540 0.02130 0.01431 -0.0258 0.9726 0.0342
-8.000 -0.7259 0.02085 0.01380 -0.0266 0.9719 0.0358
-7.750 -0.7161 0.02062 0.01351 -0.0232 0.9670 0.0367
-7.500 -0.7021 0.01963 0.01250 -0.0211 0.9642 0.0391
-7.250 -0.6793 0.01916 0.01202 -0.0207 0.9624 0.0411
-7.000 -0.6534 0.01875 0.01157 -0.0209 0.9611 0.0433
-6.750 -0.6250 0.01841 0.01118 -0.0216 0.9600 0.0452
-6.500 -0.5999 0.01774 0.01050 -0.0217 0.9590 0.0488
-6.250 -0.5932 0.01751 0.01026 -0.0176 0.9541 0.0513
-6.000 -0.5767 0.01726 0.00997 -0.0156 0.9505 0.0545
-5.750 -0.5534 0.01681 0.00953 -0.0151 0.9485 0.0608
-5.500 -0.5276 0.01634 0.00913 -0.0152 0.9471 0.0742
-5.250 -0.5039 0.01570 0.00872 -0.0150 0.9459 0.1166
-5.000 -0.4816 0.01499 0.00834 -0.0145 0.9448 0.1849
-4.750 -0.4940 0.01477 0.00827 -0.0061 0.9364 0.2224
-4.500 -0.4839 0.01394 0.00789 -0.0029 0.9336 0.3208
-4.250 -0.4784 0.01290 0.00741 0.0013 0.9313 0.4464
-4.000 -0.4975 0.01248 0.00729 0.0114 0.9228 0.5168
-3.750 -0.5032 0.01150 0.00689 0.0187 0.9188 0.6431
-3.500 -0.4877 0.01095 0.00679 0.0216 0.9171 0.7454
-3.250 -0.4570 0.01086 0.00684 0.0211 0.9163 0.7915
-3.000 -0.4573 0.01106 0.00706 0.0273 0.9089 0.8104
-2.750 -0.4315 0.01109 0.00707 0.0277 0.9066 0.8279
-2.500 -0.4007 0.01115 0.00713 0.0271 0.9052 0.8435
-2.250 -0.3694 0.01127 0.00725 0.0264 0.9041 0.8581
-2.000 -0.3335 0.01149 0.00746 0.0248 0.9034 0.8686
-1.750 -0.2897 0.01199 0.00797 0.0215 0.9032 0.8781
-1.500 -0.2414 0.01288 0.00886 0.0177 0.9033 0.8887
-1.250 -0.1878 0.01347 0.00943 0.0120 0.9036 0.8901
-1.000 -0.1430 0.01366 0.00960 0.0081 0.9035 0.8909
-0.750 -0.0989 0.01377 0.00969 0.0042 0.9033 0.8916
-0.500 -0.1126 0.01372 0.00964 0.0133 0.8951 0.9016
-0.250 -0.0727 0.01380 0.00971 0.0104 0.8940 0.9022
0.000 -0.0314 0.01384 0.00975 0.0071 0.8932 0.9026
0.250 0.0111 0.01385 0.00975 0.0035 0.8927 0.9029
0.500 0.0547 0.01382 0.00973 -0.0003 0.8921 0.9031
0.750 0.0988 0.01377 0.00969 -0.0042 0.8916 0.9033
1.000 0.1429 0.01365 0.00960 -0.0080 0.8909 0.9035
1.250 0.1877 0.01347 0.00943 -0.0120 0.8901 0.9037
1.500 0.2412 0.01288 0.00887 -0.0176 0.8887 0.9033
1.750 0.2897 0.01198 0.00796 -0.0215 0.8782 0.9032
2.000 0.3332 0.01149 0.00746 -0.0247 0.8684 0.9034
2.250 0.3693 0.01127 0.00725 -0.0264 0.8581 0.9041
2.500 0.4004 0.01115 0.00714 -0.0270 0.8437 0.9052
2.750 0.4313 0.01108 0.00707 -0.0276 0.8280 0.9066
3.000 0.4572 0.01106 0.00706 -0.0272 0.8105 0.9090
3.250 0.4569 0.01086 0.00683 -0.0210 0.7912 0.9163
3.500 0.4876 0.01094 0.00679 -0.0216 0.7454 0.9171
3.750 0.5029 0.01150 0.00689 -0.0186 0.6424 0.9188
4.000 0.4975 0.01247 0.00729 -0.0114 0.5172 0.9228
4.250 0.4785 0.01289 0.00740 -0.0013 0.4465 0.9313
4.500 0.4840 0.01394 0.00788 0.0029 0.3203 0.9336
4.750 0.4941 0.01476 0.00827 0.0060 0.2223 0.9364
5.000 0.4818 0.01498 0.00834 0.0145 0.1848 0.9448
5.250 0.5041 0.01569 0.00871 0.0149 0.1166 0.9460
5.500 0.5277 0.01633 0.00913 0.0151 0.0741 0.9472
5.750 0.5535 0.01680 0.00953 0.0151 0.0607 0.9486
6.000 0.5767 0.01725 0.00996 0.0156 0.0544 0.9506
6.250 0.5929 0.01750 0.01025 0.0177 0.0512 0.9542
6.500 0.6003 0.01773 0.01049 0.0216 0.0487 0.9590
6.750 0.6253 0.01841 0.01118 0.0215 0.0452 0.9600
7.000 0.6538 0.01875 0.01157 0.0208 0.0433 0.9611
7.250 0.6796 0.01916 0.01201 0.0206 0.0411 0.9624
7.500 0.7024 0.01962 0.01249 0.0210 0.0391 0.9642
7.750 0.7165 0.02058 0.01348 0.0231 0.0367 0.9671
8.000 0.7264 0.02086 0.01380 0.0265 0.0358 0.9719
8.250 0.7545 0.02130 0.01431 0.0257 0.0342 0.9726
8.500 0.7811 0.02179 0.01485 0.0252 0.0325 0.9735
8.750 0.8062 0.02237 0.01543 0.0249 0.0309 0.9745
9.000 0.8308 0.02358 0.01668 0.0247 0.0290 0.9755
9.250 0.8558 0.02402 0.01723 0.0246 0.0279 0.9771
9.500 0.8786 0.02462 0.01790 0.0249 0.0266 0.9790
9.750 0.8949 0.02518 0.01851 0.0265 0.0256 0.9820
10.000 0.9127 0.02578 0.01912 0.0276 0.0246 0.9841
10.250 0.9397 0.02735 0.02078 0.0268 0.0232 0.9845
10.500 0.9632 0.02787 0.02144 0.0267 0.0223 0.9855
10.750 0.9862 0.02865 0.02235 0.0267 0.0214 0.9867
11.000 1.0069 0.02945 0.02324 0.0270 0.0206 0.9881
11.250 1.0249 0.03018 0.02403 0.0277 0.0199 0.9898
11.500 1.0414 0.03111 0.02500 0.0287 0.0193 0.9916
11.750 1.0562 0.03351 0.02759 0.0297 0.0186 0.9929
12.000 1.0687 0.03448 0.02878 0.0313 0.0181 0.9947
12.250 1.0822 0.03581 0.03032 0.0323 0.0175 0.9958
12.500 1.0935 0.03716 0.03186 0.0336 0.0169 0.9972
12.750 1.1036 0.03846 0.03329 0.0349 0.0164 0.9986
13.000 1.1124 0.03985 0.03482 0.0362 0.0160 0.9999
13.250 1.1088 0.04106 0.03613 0.0400 0.0158 1.0000
13.500 1.1035 0.04218 0.03733 0.0441 0.0156 1.0000
13.750 1.0973 0.04347 0.03870 0.0481 0.0154 1.0000
14.000 1.0890 0.04507 0.04041 0.0520 0.0152 1.0000
14.250 1.0767 0.04716 0.04262 0.0560 0.0151 1.0000
14.500 1.0588 0.04991 0.04553 0.0601 0.0149 1.0000
14.750 1.0343 0.05342 0.04926 0.0642 0.0148 1.0000
15.000 1.0059 0.05748 0.05353 0.0677 0.0148 1.0000
15.250 0.9827 0.06118 0.05740 0.0702 0.0147 1.0000
15.500 0.9582 0.06543 0.06184 0.0718 0.0147 1.0000
15.750 0.9317 0.07044 0.06703 0.0724 0.0147 1.0000
16.000 0.9028 0.07651 0.07326 0.0717 0.0147 1.0000
16.250 0.8756 0.08322 0.08013 0.0697 0.0148 1.0000
16.500 0.8514 0.09041 0.08747 0.0666 0.0148 1.0000
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Polar data table (+)
Polar graphs
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