RAF 30 MOD AIRFOIL (raf30md-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 30 MOD AIRFOIL (raf30md-il) Reynolds number: 1,000,000 Max Cl/Cd: 65.38 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf30md-il-1000000-n5.txt Download as CSV file: xf-raf30md-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 30 MOD 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
------ -------- --------- --------- -------- -------- --------
-12.750 -1.0078 0.05357 0.05172 -0.0215 1.0000 0.0021
-12.500 -1.0309 0.04641 0.04439 -0.0270 1.0000 0.0021
-12.250 -1.0552 0.04134 0.03912 -0.0282 1.0000 0.0021
-12.000 -1.0770 0.03774 0.03531 -0.0259 1.0000 0.0021
-11.750 -1.0922 0.03454 0.03185 -0.0225 1.0000 0.0021
-11.500 -1.1000 0.03097 0.02795 -0.0199 1.0000 0.0022
-11.250 -1.0969 0.02832 0.02502 -0.0179 1.0000 0.0022
-11.000 -1.0893 0.02599 0.02242 -0.0161 1.0000 0.0023
-10.750 -1.0760 0.02434 0.02057 -0.0147 1.0000 0.0024
-10.500 -1.0602 0.02292 0.01894 -0.0135 1.0000 0.0024
-10.250 -1.0424 0.02175 0.01762 -0.0125 1.0000 0.0025
-10.000 -1.0232 0.02075 0.01649 -0.0115 1.0000 0.0026
-9.750 -1.0041 0.01967 0.01526 -0.0105 1.0000 0.0027
-9.500 -0.9837 0.01878 0.01425 -0.0096 1.0000 0.0028
-9.250 -0.9626 0.01798 0.01334 -0.0088 1.0000 0.0030
-9.000 -0.9413 0.01718 0.01243 -0.0079 1.0000 0.0031
-8.750 -0.9195 0.01645 0.01158 -0.0071 1.0000 0.0033
-8.500 -0.8980 0.01565 0.01066 -0.0062 1.0000 0.0034
-8.250 -0.8757 0.01500 0.00990 -0.0054 1.0000 0.0035
-8.000 -0.8542 0.01422 0.00900 -0.0044 1.0000 0.0036
-7.750 -0.8331 0.01337 0.00805 -0.0033 1.0000 0.0040
-7.500 -0.8104 0.01282 0.00741 -0.0025 1.0000 0.0043
-7.250 -0.7874 0.01234 0.00688 -0.0016 1.0000 0.0045
-7.000 -0.7643 0.01190 0.00638 -0.0008 1.0000 0.0049
-6.750 -0.7411 0.01147 0.00589 0.0000 1.0000 0.0052
-6.500 -0.7176 0.01110 0.00546 0.0008 1.0000 0.0056
-6.250 -0.6946 0.01064 0.00494 0.0017 1.0000 0.0061
-6.000 -0.6713 0.01026 0.00456 0.0025 1.0000 0.0071
-5.750 -0.6478 0.00994 0.00421 0.0034 1.0000 0.0080
-5.500 -0.6241 0.00965 0.00386 0.0042 1.0000 0.0087
-5.250 -0.6007 0.00932 0.00351 0.0051 1.0000 0.0106
-5.000 -0.5729 0.00904 0.00327 0.0049 0.9991 0.0135
-4.750 -0.5410 0.00877 0.00305 0.0039 0.9966 0.0198
-4.500 -0.5092 0.00860 0.00285 0.0029 0.9937 0.0236
-4.250 -0.4777 0.00846 0.00270 0.0020 0.9902 0.0252
-4.000 -0.4447 0.00833 0.00256 0.0008 0.9869 0.0259
-3.750 -0.4136 0.00818 0.00241 0.0000 0.9817 0.0262
-3.500 -0.3801 0.00793 0.00211 -0.0013 0.9769 0.0279
-3.250 -0.3467 0.00772 0.00188 -0.0026 0.9694 0.0309
-3.000 -0.3123 0.00753 0.00168 -0.0041 0.9590 0.0332
-2.750 -0.2784 0.00737 0.00151 -0.0054 0.9423 0.0367
-2.500 -0.2487 0.00709 0.00132 -0.0058 0.9163 0.0738
-2.250 -0.2228 0.00690 0.00117 -0.0054 0.8844 0.1101
-1.500 -0.1488 0.00631 0.00081 -0.0035 0.8008 0.2631
-1.250 -0.1240 0.00605 0.00072 -0.0029 0.7800 0.3330
-1.000 -0.0984 0.00589 0.00066 -0.0025 0.7597 0.3792
-0.750 -0.0729 0.00574 0.00060 -0.0021 0.7398 0.4310
-0.500 -0.0484 0.00550 0.00056 -0.0015 0.7147 0.5100
-0.250 -0.0243 0.00544 0.00054 -0.0007 0.6682 0.5686
0.000 0.0001 0.00545 0.00053 0.0000 0.6171 0.6154
0.250 0.0243 0.00542 0.00054 0.0007 0.5701 0.6703
0.500 0.0484 0.00550 0.00056 0.0015 0.5087 0.7150
0.750 0.0730 0.00573 0.00060 0.0021 0.4323 0.7396
1.000 0.0985 0.00589 0.00066 0.0025 0.3798 0.7599
1.250 0.1241 0.00606 0.00072 0.0029 0.3314 0.7800
1.500 0.1490 0.00629 0.00081 0.0034 0.2661 0.8008
1.750 0.1735 0.00656 0.00091 0.0040 0.1984 0.8248
2.000 0.1980 0.00676 0.00103 0.0047 0.1463 0.8531
2.250 0.2228 0.00691 0.00117 0.0054 0.1088 0.8842
2.500 0.2488 0.00709 0.00132 0.0058 0.0737 0.9161
2.750 0.2784 0.00737 0.00151 0.0054 0.0367 0.9421
3.000 0.3123 0.00753 0.00169 0.0041 0.0330 0.9590
3.250 0.3466 0.00771 0.00188 0.0026 0.0310 0.9694
3.500 0.3798 0.00793 0.00211 0.0014 0.0280 0.9768
3.750 0.4134 0.00818 0.00240 0.0001 0.0261 0.9816
4.000 0.4445 0.00833 0.00256 -0.0007 0.0259 0.9868
4.250 0.4775 0.00845 0.00269 -0.0019 0.0252 0.9901
4.500 0.5090 0.00860 0.00285 -0.0028 0.0236 0.9936
4.750 0.5408 0.00877 0.00304 -0.0038 0.0196 0.9965
5.000 0.5726 0.00904 0.00327 -0.0048 0.0135 0.9989
5.250 0.6009 0.00933 0.00351 -0.0051 0.0106 1.0000
5.500 0.6243 0.00965 0.00385 -0.0042 0.0087 1.0000
5.750 0.6480 0.00994 0.00421 -0.0034 0.0079 1.0000
6.000 0.6715 0.01027 0.00456 -0.0026 0.0072 1.0000
6.250 0.6948 0.01064 0.00495 -0.0017 0.0063 1.0000
6.500 0.7177 0.01110 0.00546 -0.0008 0.0056 1.0000
6.750 0.7411 0.01148 0.00590 0.0000 0.0052 1.0000
7.000 0.7643 0.01192 0.00640 0.0008 0.0049 1.0000
7.250 0.7874 0.01236 0.00690 0.0017 0.0046 1.0000
7.500 0.8104 0.01284 0.00743 0.0025 0.0043 1.0000
7.750 0.8331 0.01338 0.00806 0.0033 0.0040 1.0000
8.000 0.8546 0.01414 0.00892 0.0043 0.0037 1.0000
8.250 0.8754 0.01503 0.00994 0.0054 0.0036 1.0000
8.500 0.8977 0.01569 0.01070 0.0062 0.0034 1.0000
8.750 0.9194 0.01644 0.01157 0.0071 0.0033 1.0000
9.000 0.9410 0.01720 0.01244 0.0080 0.0031 1.0000
9.250 0.9622 0.01802 0.01339 0.0089 0.0030 1.0000
9.500 0.9834 0.01881 0.01429 0.0097 0.0028 1.0000
9.750 1.0033 0.01979 0.01540 0.0106 0.0027 1.0000
10.000 1.0234 0.02069 0.01642 0.0115 0.0026 1.0000
10.250 1.0415 0.02188 0.01777 0.0126 0.0025 1.0000
10.500 1.0591 0.02307 0.01911 0.0137 0.0024 1.0000
10.750 1.0758 0.02433 0.02056 0.0148 0.0024 1.0000
11.000 1.0890 0.02601 0.02245 0.0162 0.0023 1.0000
11.250 1.0985 0.02805 0.02472 0.0178 0.0022 1.0000
11.500 1.0991 0.03105 0.02804 0.0200 0.0022 1.0000
11.750 1.0935 0.03436 0.03166 0.0225 0.0021 1.0000
12.000 1.0809 0.03741 0.03495 0.0256 0.0021 1.0000
12.250 1.0606 0.04083 0.03857 0.0282 0.0021 1.0000
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Polar data table (+)
Polar graphs
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