RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 8 AIRFOIL (rg8-il) Reynolds number: 500,000 Max Cl/Cd: 96.49 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg8-il-500000.txt Download as CSV file: xf-rg8-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RG 8 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3697 0.10206 0.09986 -0.0334 1.0000 0.0278
-10.750 -0.3772 0.09656 0.09438 -0.0353 1.0000 0.0294
-8.250 -0.6952 0.03227 0.02824 -0.0509 0.9986 0.0176
-8.000 -0.6660 0.02972 0.02536 -0.0531 0.9962 0.0174
-7.750 -0.6367 0.02666 0.02194 -0.0554 0.9943 0.0174
-7.500 -0.6100 0.02375 0.01868 -0.0566 0.9917 0.0174
-7.250 -0.5826 0.02060 0.01517 -0.0579 0.9893 0.0177
-7.000 -0.5526 0.01842 0.01280 -0.0592 0.9873 0.0183
-6.750 -0.5188 0.01745 0.01176 -0.0610 0.9855 0.0194
-6.500 -0.4838 0.01647 0.01069 -0.0629 0.9841 0.0201
-6.250 -0.4539 0.01556 0.00969 -0.0636 0.9808 0.0208
-6.000 -0.4220 0.01474 0.00878 -0.0647 0.9776 0.0215
-5.750 -0.3876 0.01405 0.00800 -0.0663 0.9752 0.0224
-5.500 -0.3516 0.01346 0.00734 -0.0682 0.9733 0.0231
-5.250 -0.3153 0.01253 0.00636 -0.0704 0.9718 0.0257
-5.000 -0.2867 0.01204 0.00583 -0.0706 0.9669 0.0278
-4.750 -0.2526 0.01162 0.00534 -0.0720 0.9636 0.0305
-4.500 -0.2165 0.01091 0.00472 -0.0739 0.9613 0.0498
-4.250 -0.1793 0.01029 0.00434 -0.0762 0.9596 0.0996
-4.000 -0.1484 0.00986 0.00405 -0.0770 0.9551 0.1361
-3.750 -0.1156 0.00943 0.00377 -0.0782 0.9509 0.1788
-3.500 -0.0792 0.00893 0.00349 -0.0803 0.9483 0.2367
-3.250 -0.0419 0.00827 0.00318 -0.0826 0.9464 0.3335
-3.000 -0.0095 0.00764 0.00297 -0.0839 0.9425 0.4486
-2.750 0.0227 0.00733 0.00284 -0.0847 0.9373 0.5170
-2.500 0.0605 0.00713 0.00269 -0.0867 0.9341 0.5517
-2.250 0.0995 0.00695 0.00254 -0.0889 0.9313 0.5788
-2.000 0.1288 0.00684 0.00244 -0.0890 0.9224 0.5979
-1.750 0.1672 0.00671 0.00229 -0.0910 0.9174 0.6136
-1.500 0.1979 0.00662 0.00220 -0.0914 0.9070 0.6257
-1.250 0.2314 0.00655 0.00211 -0.0924 0.8972 0.6381
-1.000 0.2648 0.00650 0.00201 -0.0934 0.8862 0.6502
-0.750 0.2961 0.00647 0.00196 -0.0939 0.8731 0.6612
-0.500 0.3256 0.00645 0.00192 -0.0940 0.8582 0.6710
-0.250 0.3541 0.00647 0.00189 -0.0939 0.8421 0.6811
0.000 0.3819 0.00650 0.00188 -0.0937 0.8248 0.6913
0.250 0.4092 0.00653 0.00188 -0.0934 0.8068 0.7011
0.500 0.4362 0.00659 0.00189 -0.0930 0.7883 0.7112
0.750 0.4627 0.00666 0.00191 -0.0926 0.7689 0.7214
1.000 0.4886 0.00672 0.00194 -0.0920 0.7485 0.7313
1.250 0.5144 0.00682 0.00198 -0.0914 0.7280 0.7415
1.500 0.5401 0.00691 0.00203 -0.0908 0.7063 0.7518
1.750 0.5653 0.00701 0.00209 -0.0901 0.6845 0.7613
2.000 0.5906 0.00712 0.00215 -0.0894 0.6620 0.7718
2.500 0.6401 0.00737 0.00233 -0.0880 0.6150 0.7954
2.750 0.6644 0.00751 0.00243 -0.0871 0.5912 0.8086
3.000 0.6884 0.00765 0.00254 -0.0862 0.5669 0.8234
3.250 0.7122 0.00779 0.00267 -0.0853 0.5421 0.8406
3.500 0.7347 0.00794 0.00280 -0.0841 0.5171 0.8603
3.750 0.7562 0.00809 0.00294 -0.0826 0.4919 0.8850
4.000 0.7750 0.00819 0.00306 -0.0805 0.4666 0.9203
4.250 0.8038 0.00833 0.00317 -0.0807 0.4387 1.0000
4.500 0.8293 0.00863 0.00335 -0.0804 0.4117 1.0000
4.750 0.8543 0.00894 0.00355 -0.0800 0.3849 1.0000
5.000 0.8788 0.00927 0.00378 -0.0794 0.3561 1.0000
5.250 0.9030 0.00963 0.00402 -0.0789 0.3265 1.0000
5.500 0.9271 0.01001 0.00428 -0.0783 0.2985 1.0000
6.000 0.9746 0.01080 0.00487 -0.0771 0.2442 1.0000
6.250 0.9974 0.01128 0.00521 -0.0763 0.2141 1.0000
6.500 1.0199 0.01179 0.00558 -0.0755 0.1824 1.0000
6.750 1.0417 0.01235 0.00598 -0.0746 0.1508 1.0000
7.000 1.0636 0.01291 0.00642 -0.0737 0.1253 1.0000
7.250 1.0849 0.01350 0.00688 -0.0728 0.1022 1.0000
7.500 1.1065 0.01406 0.00735 -0.0719 0.0823 1.0000
7.750 1.1270 0.01470 0.00789 -0.0708 0.0646 1.0000
8.000 1.1480 0.01527 0.00842 -0.0697 0.0510 1.0000
8.250 1.1673 0.01600 0.00906 -0.0684 0.0357 1.0000
8.500 1.1836 0.01700 0.00997 -0.0666 0.0212 1.0000
8.750 1.2007 0.01788 0.01089 -0.0648 0.0166 1.0000
9.000 1.2169 0.01878 0.01183 -0.0630 0.0144 1.0000
9.250 1.2330 0.01963 0.01276 -0.0612 0.0131 1.0000
9.500 1.2495 0.02035 0.01355 -0.0594 0.0121 1.0000
9.750 1.2630 0.02116 0.01443 -0.0571 0.0115 1.0000
10.000 1.2736 0.02212 0.01547 -0.0545 0.0109 1.0000
10.250 1.2786 0.02343 0.01688 -0.0511 0.0104 1.0000
10.500 1.2801 0.02503 0.01860 -0.0474 0.0101 1.0000
10.750 1.2902 0.02606 0.01973 -0.0451 0.0099 1.0000
11.000 1.2974 0.02733 0.02110 -0.0425 0.0097 1.0000
11.250 1.3046 0.02863 0.02252 -0.0401 0.0095 1.0000
11.500 1.3096 0.03016 0.02417 -0.0377 0.0093 1.0000
11.750 1.3141 0.03179 0.02593 -0.0354 0.0091 1.0000
12.000 1.3175 0.03361 0.02787 -0.0333 0.0090 1.0000
12.250 1.3205 0.03552 0.02991 -0.0314 0.0088 1.0000
12.500 1.3223 0.03767 0.03221 -0.0296 0.0087 1.0000
12.750 1.3233 0.03997 0.03464 -0.0281 0.0085 1.0000
13.000 1.3231 0.04251 0.03734 -0.0269 0.0084 1.0000
13.250 1.3219 0.04527 0.04024 -0.0259 0.0083 1.0000
13.500 1.3190 0.04836 0.04350 -0.0253 0.0083 1.0000
13.750 1.3148 0.05174 0.04704 -0.0249 0.0082 1.0000
14.000 1.3090 0.05550 0.05098 -0.0250 0.0082 1.0000
14.250 1.3017 0.05960 0.05526 -0.0256 0.0082 1.0000
14.500 1.2935 0.06402 0.05984 -0.0266 0.0081 1.0000
14.750 1.2824 0.06915 0.06516 -0.0282 0.0081 1.0000
15.000 1.2728 0.07426 0.07043 -0.0303 0.0081 1.0000
15.250 1.2606 0.08012 0.07646 -0.0329 0.0080 1.0000
15.500 1.2470 0.08655 0.08306 -0.0362 0.0080 1.0000
15.750 1.2313 0.09373 0.09044 -0.0401 0.0081 1.0000
16.000 1.2104 0.10243 0.09935 -0.0450 0.0082 1.0000
16.250 1.1932 0.11072 0.10782 -0.0500 0.0082 1.0000
16.500 1.1598 0.12349 0.12087 -0.0581 0.0084 1.0000
16.750 1.1295 0.13638 0.13399 -0.0665 0.0087 1.0000
17.000 1.0929 0.15198 0.14981 -0.0765 0.0090 1.0000
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