NACA 5-H-10 AIRFOIL (n5h10-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-10 AIRFOIL (n5h10-il) Reynolds number: 1,000,000 Max Cl/Cd: 69 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h10-il-1000000-n5.txt Download as CSV file: xf-n5h10-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-10 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5440 0.10236 0.10009 -0.0049 0.7745 0.0039
-10.500 -0.5431 0.09837 0.09610 -0.0070 0.7717 0.0041
-10.000 -0.9140 0.02521 0.02116 -0.0129 0.7667 0.0036
-9.750 -0.8998 0.02290 0.01857 -0.0113 0.7640 0.0038
-9.500 -0.8810 0.02146 0.01694 -0.0103 0.7608 0.0039
-9.250 -0.8610 0.02014 0.01543 -0.0093 0.7575 0.0040
-9.000 -0.8396 0.01910 0.01421 -0.0085 0.7542 0.0041
-8.750 -0.8172 0.01820 0.01314 -0.0078 0.7512 0.0043
-8.500 -0.7942 0.01733 0.01214 -0.0072 0.7480 0.0044
-8.250 -0.7709 0.01649 0.01115 -0.0065 0.7444 0.0046
-8.000 -0.7471 0.01577 0.01029 -0.0060 0.7407 0.0048
-7.750 -0.7229 0.01509 0.00948 -0.0054 0.7371 0.0050
-7.500 -0.6981 0.01449 0.00876 -0.0050 0.7329 0.0052
-7.250 -0.6730 0.01399 0.00816 -0.0046 0.7284 0.0054
-7.000 -0.6486 0.01329 0.00735 -0.0041 0.7243 0.0060
-6.750 -0.6232 0.01282 0.00681 -0.0037 0.7201 0.0064
-6.500 -0.5976 0.01241 0.00633 -0.0034 0.7149 0.0068
-6.250 -0.5720 0.01200 0.00583 -0.0030 0.7098 0.0072
-6.000 -0.5461 0.01163 0.00539 -0.0027 0.7043 0.0076
-5.750 -0.5204 0.01125 0.00493 -0.0024 0.6982 0.0082
-5.500 -0.4947 0.01088 0.00452 -0.0020 0.6929 0.0092
-5.250 -0.4685 0.01060 0.00420 -0.0017 0.6870 0.0105
-5.000 -0.4423 0.01037 0.00389 -0.0015 0.6813 0.0115
-4.750 -0.4160 0.01011 0.00364 -0.0012 0.6757 0.0137
-4.500 -0.3892 0.00996 0.00350 -0.0011 0.6697 0.0159
-4.250 -0.3624 0.00982 0.00331 -0.0009 0.6642 0.0172
-4.000 -0.3358 0.00963 0.00311 -0.0007 0.6585 0.0196
-3.750 -0.3087 0.00954 0.00301 -0.0007 0.6532 0.0218
-3.500 -0.2815 0.00943 0.00288 -0.0006 0.6487 0.0238
-3.250 -0.2543 0.00934 0.00276 -0.0005 0.6440 0.0253
-3.000 -0.2271 0.00927 0.00265 -0.0004 0.6395 0.0261
-2.750 -0.1997 0.00921 0.00257 -0.0004 0.6356 0.0266
-2.500 -0.1733 0.00898 0.00230 -0.0002 0.6311 0.0277
-2.250 -0.1470 0.00877 0.00203 0.0001 0.6257 0.0293
-2.000 -0.1202 0.00862 0.00185 0.0003 0.6207 0.0301
-1.750 -0.0932 0.00849 0.00168 0.0004 0.6159 0.0307
-1.500 -0.0662 0.00839 0.00154 0.0006 0.6116 0.0313
-1.250 -0.0391 0.00829 0.00142 0.0007 0.6075 0.0319
-1.000 -0.0119 0.00820 0.00132 0.0007 0.6036 0.0330
-0.750 0.0154 0.00811 0.00123 0.0008 0.6002 0.0342
-0.500 0.0427 0.00805 0.00115 0.0009 0.5968 0.0356
-0.250 0.0700 0.00799 0.00109 0.0009 0.5934 0.0384
0.000 0.0969 0.00785 0.00105 0.0010 0.5897 0.0643
0.250 0.1224 0.00759 0.00100 0.0014 0.5855 0.1368
0.500 0.1460 0.00721 0.00096 0.0020 0.5813 0.2645
0.750 0.1605 0.00615 0.00086 0.0042 0.5763 0.5714
1.000 0.1710 0.00533 0.00091 0.0080 0.5713 0.8431
1.250 0.1983 0.00538 0.00095 0.0081 0.5677 0.8553
1.500 0.2255 0.00545 0.00099 0.0082 0.5583 0.8648
1.750 0.2525 0.00553 0.00104 0.0084 0.5411 0.8708
2.000 0.2794 0.00563 0.00109 0.0086 0.5264 0.8774
2.250 0.3061 0.00573 0.00115 0.0088 0.5087 0.8830
2.500 0.3322 0.00590 0.00123 0.0090 0.4797 0.8886
2.750 0.3559 0.00632 0.00138 0.0096 0.4059 0.8935
3.000 0.3774 0.00705 0.00170 0.0103 0.3067 0.8963
3.250 0.4034 0.00731 0.00185 0.0104 0.2761 0.8976
3.500 0.4293 0.00758 0.00200 0.0105 0.2408 0.8987
3.750 0.4507 0.00834 0.00235 0.0111 0.1389 0.8995
4.000 0.4762 0.00865 0.00254 0.0112 0.1090 0.9001
4.250 0.5020 0.00890 0.00271 0.0113 0.0894 0.9006
4.500 0.5282 0.00911 0.00287 0.0114 0.0765 0.9013
4.750 0.5522 0.00953 0.00312 0.0117 0.0406 0.9022
5.000 0.5780 0.00976 0.00334 0.0118 0.0334 0.9028
5.250 0.6042 0.00995 0.00353 0.0118 0.0317 0.9034
5.500 0.6302 0.01014 0.00375 0.0119 0.0304 0.9040
5.750 0.6559 0.01036 0.00399 0.0120 0.0290 0.9046
6.000 0.6813 0.01060 0.00424 0.0122 0.0275 0.9052
6.500 0.7307 0.01115 0.00485 0.0127 0.0240 0.9068
6.750 0.7547 0.01147 0.00523 0.0131 0.0227 0.9078
7.000 0.7801 0.01164 0.00542 0.0132 0.0223 0.9087
7.250 0.8052 0.01183 0.00564 0.0133 0.0212 0.9097
7.500 0.8296 0.01207 0.00590 0.0136 0.0193 0.9108
7.750 0.8529 0.01236 0.00619 0.0140 0.0158 0.9120
8.000 0.8754 0.01271 0.00654 0.0145 0.0126 0.9134
8.250 0.8970 0.01311 0.00691 0.0152 0.0103 0.9149
8.500 0.9183 0.01350 0.00734 0.0159 0.0092 0.9165
8.750 0.9391 0.01390 0.00779 0.0166 0.0084 0.9183
9.250 0.9764 0.01489 0.00886 0.0188 0.0065 0.9233
9.500 0.9953 0.01531 0.00935 0.0198 0.0061 0.9268
9.750 1.0125 0.01581 0.00992 0.0210 0.0057 0.9315
10.000 1.0285 0.01632 0.01052 0.0224 0.0053 0.9392
10.250 1.0501 0.01698 0.01128 0.0223 0.0049 0.9505
10.500 1.0789 0.01802 0.01241 0.0201 0.0046 0.9620
11.000 1.1428 0.01997 0.01455 0.0143 0.0041 0.9931
11.250 1.1544 0.02088 0.01552 0.0157 0.0039 1.0000
11.500 1.1645 0.02189 0.01661 0.0171 0.0038 1.0000
11.750 1.1761 0.02284 0.01762 0.0183 0.0036 1.0000
12.000 1.1863 0.02395 0.01879 0.0195 0.0035 1.0000
12.250 1.1982 0.02494 0.01987 0.0204 0.0033 1.0000
12.500 1.2099 0.02597 0.02094 0.0213 0.0032 1.0000
12.750 1.2165 0.02748 0.02254 0.0225 0.0029 1.0000
13.000 1.2214 0.02917 0.02433 0.0236 0.0029 1.0000
13.250 1.2279 0.03075 0.02602 0.0245 0.0028 1.0000
13.500 1.2378 0.03206 0.02742 0.0252 0.0027 1.0000
13.750 1.2428 0.03385 0.02930 0.0259 0.0027 1.0000
14.000 1.2469 0.03575 0.03133 0.0266 0.0027 1.0000
14.250 1.2501 0.03781 0.03350 0.0272 0.0026 1.0000
14.500 1.2559 0.03963 0.03541 0.0275 0.0026 1.0000
14.750 1.2548 0.04221 0.03813 0.0279 0.0025 1.0000
15.000 1.2582 0.04438 0.04040 0.0280 0.0024 1.0000
15.250 1.2544 0.04739 0.04355 0.0281 0.0024 1.0000
15.500 1.2558 0.04995 0.04623 0.0279 0.0024 1.0000
15.750 1.2521 0.05325 0.04965 0.0274 0.0024 1.0000
16.000 1.2461 0.05697 0.05350 0.0267 0.0023 1.0000
16.250 1.2386 0.06106 0.05773 0.0257 0.0023 1.0000
16.500 1.2319 0.06518 0.06197 0.0244 0.0022 1.0000
16.750 1.2169 0.07074 0.06770 0.0225 0.0022 1.0000
17.000 1.2087 0.07554 0.07261 0.0206 0.0022 1.0000
17.250 1.1871 0.08275 0.08000 0.0175 0.0022 1.0000
17.500 1.1702 0.08966 0.08704 0.0142 0.0022 1.0000
17.750 1.1500 0.09754 0.09507 0.0103 0.0022 1.0000
18.000 1.1251 0.10664 0.10432 0.0057 0.0022 1.0000
18.250 1.0897 0.11838 0.11623 -0.0002 0.0023 1.0000
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Polar data table (+)
Polar graphs
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