RUTAN WING AIRFOIL (amsoil2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN WING AIRFOIL (amsoil2-il) Reynolds number: 500,000 Max Cl/Cd: 61.69 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil2-il-500000-n5.txt Download as CSV file: xf-amsoil2-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN WING 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.1416 0.08487 0.08141 -0.0222 1.0000 0.0201
-16.500 -1.1979 0.06878 0.06501 -0.0333 1.0000 0.0200
-16.250 -1.2265 0.05971 0.05571 -0.0396 1.0000 0.0200
-16.000 -1.2439 0.05347 0.04926 -0.0434 1.0000 0.0201
-15.750 -1.2550 0.04872 0.04432 -0.0457 1.0000 0.0202
-15.500 -1.2616 0.04491 0.04033 -0.0471 1.0000 0.0204
-15.250 -1.2657 0.04172 0.03703 -0.0478 1.0000 0.0206
-15.000 -1.2660 0.03913 0.03434 -0.0480 1.0000 0.0207
-14.750 -1.2634 0.03697 0.03208 -0.0478 1.0000 0.0209
-14.500 -1.2588 0.03511 0.03013 -0.0474 1.0000 0.0211
-14.250 -1.2526 0.03348 0.02840 -0.0467 1.0000 0.0214
-14.000 -1.2454 0.03201 0.02683 -0.0458 1.0000 0.0216
-13.750 -1.2371 0.03069 0.02541 -0.0446 1.0000 0.0219
-13.500 -1.2282 0.02949 0.02411 -0.0432 1.0000 0.0221
-13.250 -1.2182 0.02842 0.02293 -0.0415 1.0000 0.0224
-13.000 -1.2048 0.02739 0.02179 -0.0403 1.0000 0.0228
-12.750 -1.1892 0.02641 0.02068 -0.0393 1.0000 0.0232
-12.500 -1.1720 0.02548 0.01962 -0.0384 1.0000 0.0235
-12.250 -1.1542 0.02457 0.01861 -0.0376 1.0000 0.0238
-12.000 -1.1357 0.02371 0.01772 -0.0368 1.0000 0.0242
-11.750 -1.1152 0.02302 0.01698 -0.0362 1.0000 0.0247
-11.500 -1.0938 0.02239 0.01630 -0.0357 1.0000 0.0251
-11.250 -1.0718 0.02176 0.01561 -0.0353 1.0000 0.0257
-11.000 -1.0496 0.02113 0.01491 -0.0348 1.0000 0.0262
-10.750 -1.0270 0.02049 0.01419 -0.0344 1.0000 0.0268
-10.500 -1.0040 0.01989 0.01349 -0.0340 1.0000 0.0273
-10.250 -0.9810 0.01923 0.01278 -0.0336 0.9973 0.0278
-9.750 -0.9235 0.01809 0.01158 -0.0351 0.9727 0.0290
-9.500 -0.8962 0.01762 0.01106 -0.0354 0.9626 0.0297
-9.250 -0.8704 0.01719 0.01055 -0.0353 0.9532 0.0306
-9.000 -0.8458 0.01678 0.01006 -0.0348 0.9436 0.0313
-8.750 -0.8220 0.01630 0.00953 -0.0342 0.9348 0.0319
-8.500 -0.7985 0.01586 0.00906 -0.0336 0.9267 0.0326
-8.250 -0.7737 0.01548 0.00865 -0.0331 0.9192 0.0334
-8.000 -0.7490 0.01514 0.00825 -0.0326 0.9119 0.0343
-7.500 -0.6978 0.01449 0.00747 -0.0319 0.8988 0.0362
-7.250 -0.6729 0.01408 0.00705 -0.0315 0.8927 0.0372
-7.000 -0.6466 0.01375 0.00670 -0.0313 0.8869 0.0383
-6.750 -0.6202 0.01346 0.00638 -0.0311 0.8811 0.0395
-6.500 -0.5938 0.01319 0.00606 -0.0308 0.8758 0.0408
-6.250 -0.5671 0.01287 0.00572 -0.0306 0.8706 0.0422
-6.000 -0.5402 0.01258 0.00544 -0.0305 0.8649 0.0436
-5.750 -0.5132 0.01234 0.00516 -0.0304 0.8596 0.0453
-5.500 -0.4860 0.01211 0.00489 -0.0302 0.8550 0.0471
-5.250 -0.4585 0.01184 0.00464 -0.0303 0.8501 0.0494
-5.000 -0.4309 0.01162 0.00441 -0.0302 0.8451 0.0519
-4.750 -0.4034 0.01141 0.00418 -0.0301 0.8404 0.0544
-4.500 -0.3756 0.01120 0.00397 -0.0301 0.8358 0.0576
-4.250 -0.3475 0.01101 0.00378 -0.0302 0.8306 0.0611
-4.000 -0.3196 0.01080 0.00360 -0.0302 0.8255 0.0653
-3.750 -0.2917 0.01065 0.00342 -0.0302 0.8207 0.0694
-3.500 -0.2634 0.01046 0.00327 -0.0303 0.8159 0.0745
-3.250 -0.2350 0.01030 0.00312 -0.0304 0.8110 0.0799
-3.000 -0.2066 0.01014 0.00298 -0.0304 0.8064 0.0866
-2.750 -0.1784 0.00999 0.00285 -0.0305 0.8021 0.0936
-2.500 -0.1497 0.00984 0.00273 -0.0306 0.7975 0.1019
-2.250 -0.1210 0.00968 0.00263 -0.0308 0.7928 0.1130
-2.000 -0.0925 0.00952 0.00252 -0.0309 0.7885 0.1275
-1.750 -0.0641 0.00934 0.00242 -0.0310 0.7844 0.1483
-1.500 -0.0355 0.00911 0.00234 -0.0312 0.7799 0.1806
-1.250 -0.0072 0.00879 0.00224 -0.0315 0.7750 0.2346
-1.000 0.0198 0.00810 0.00206 -0.0317 0.7705 0.3776
-0.750 0.0460 0.00734 0.00196 -0.0318 0.7663 0.5634
-0.500 0.0739 0.00709 0.00198 -0.0318 0.7581 0.6387
-0.250 0.1018 0.00700 0.00197 -0.0315 0.7471 0.6779
0.000 0.1303 0.00695 0.00197 -0.0314 0.7345 0.7025
0.250 0.1584 0.00694 0.00196 -0.0313 0.7179 0.7237
0.500 0.1867 0.00694 0.00198 -0.0311 0.7017 0.7424
0.750 0.2150 0.00696 0.00200 -0.0310 0.6866 0.7587
1.000 0.2430 0.00699 0.00204 -0.0308 0.6685 0.7764
1.250 0.2706 0.00706 0.00209 -0.0304 0.6459 0.7946
1.500 0.2982 0.00722 0.00211 -0.0302 0.6081 0.8043
1.750 0.3240 0.00757 0.00217 -0.0298 0.5302 0.8098
2.000 0.3448 0.00878 0.00252 -0.0290 0.3273 0.8165
2.250 0.3688 0.00958 0.00283 -0.0287 0.2115 0.8230
2.500 0.3950 0.00993 0.00302 -0.0285 0.1688 0.8292
2.750 0.4220 0.01022 0.00319 -0.0284 0.1425 0.8356
3.000 0.4493 0.01045 0.00334 -0.0283 0.1248 0.8412
3.250 0.4761 0.01066 0.00350 -0.0281 0.1111 0.8471
3.500 0.5032 0.01088 0.00368 -0.0279 0.0996 0.8538
3.750 0.5302 0.01109 0.00385 -0.0278 0.0908 0.8601
4.000 0.5568 0.01129 0.00404 -0.0275 0.0842 0.8665
4.250 0.5835 0.01152 0.00424 -0.0273 0.0780 0.8734
4.500 0.6099 0.01172 0.00444 -0.0270 0.0732 0.8799
4.750 0.6358 0.01196 0.00466 -0.0266 0.0690 0.8877
5.000 0.6619 0.01216 0.00489 -0.0262 0.0656 0.8957
5.250 0.6870 0.01240 0.00512 -0.0257 0.0621 0.9048
5.500 0.7120 0.01263 0.00537 -0.0251 0.0592 0.9141
5.750 0.7368 0.01286 0.00562 -0.0245 0.0565 0.9246
6.000 0.7608 0.01312 0.00588 -0.0237 0.0540 0.9359
6.250 0.7856 0.01336 0.00615 -0.0231 0.0519 0.9485
6.500 0.8123 0.01362 0.00643 -0.0229 0.0495 0.9634
7.000 0.8694 0.01427 0.00708 -0.0237 0.0457 1.0000
7.250 0.8953 0.01460 0.00741 -0.0235 0.0440 1.0000
7.500 0.9206 0.01497 0.00776 -0.0233 0.0424 1.0000
7.750 0.9453 0.01539 0.00817 -0.0229 0.0410 1.0000
8.000 0.9703 0.01575 0.00856 -0.0226 0.0397 1.0000
8.250 0.9951 0.01613 0.00896 -0.0222 0.0383 1.0000
8.500 1.0192 0.01655 0.00937 -0.0218 0.0371 1.0000
8.750 1.0424 0.01706 0.00987 -0.0213 0.0361 1.0000
9.000 1.0661 0.01748 0.01034 -0.0208 0.0352 1.0000
9.250 1.0894 0.01793 0.01083 -0.0202 0.0342 1.0000
9.500 1.1124 0.01839 0.01131 -0.0196 0.0332 1.0000
9.750 1.1348 0.01888 0.01181 -0.0190 0.0323 1.0000
10.000 1.1557 0.01948 0.01241 -0.0181 0.0314 1.0000
10.250 1.1774 0.01999 0.01299 -0.0174 0.0307 1.0000
10.500 1.1983 0.02054 0.01359 -0.0165 0.0300 1.0000
10.750 1.2186 0.02111 0.01421 -0.0156 0.0293 1.0000
11.000 1.2381 0.02169 0.01483 -0.0146 0.0286 1.0000
11.250 1.2556 0.02231 0.01548 -0.0133 0.0281 1.0000
11.500 1.2709 0.02304 0.01623 -0.0117 0.0275 1.0000
11.750 1.2869 0.02375 0.01702 -0.0102 0.0270 1.0000
12.000 1.3031 0.02447 0.01782 -0.0089 0.0264 1.0000
12.250 1.3188 0.02523 0.01865 -0.0076 0.0258 1.0000
12.500 1.3340 0.02604 0.01952 -0.0063 0.0253 1.0000
12.750 1.3485 0.02690 0.02045 -0.0051 0.0248 1.0000
13.000 1.3621 0.02783 0.02144 -0.0038 0.0244 1.0000
13.250 1.3745 0.02888 0.02254 -0.0025 0.0240 1.0000
13.500 1.3846 0.03013 0.02383 -0.0012 0.0236 1.0000
13.750 1.3959 0.03132 0.02513 0.0000 0.0233 1.0000
14.000 1.4065 0.03258 0.02651 0.0012 0.0230 1.0000
14.250 1.4160 0.03396 0.02799 0.0023 0.0226 1.0000
14.500 1.4247 0.03544 0.02957 0.0034 0.0223 1.0000
14.750 1.4323 0.03702 0.03125 0.0044 0.0220 1.0000
15.000 1.4391 0.03872 0.03305 0.0052 0.0217 1.0000
15.250 1.4449 0.04055 0.03498 0.0060 0.0214 1.0000
15.500 1.4497 0.04251 0.03703 0.0067 0.0212 1.0000
15.750 1.4533 0.04465 0.03927 0.0072 0.0209 1.0000
16.000 1.4551 0.04705 0.04176 0.0075 0.0207 1.0000
16.250 1.4544 0.04977 0.04457 0.0077 0.0205 1.0000
16.500 1.4511 0.05290 0.04780 0.0076 0.0203 1.0000
16.750 1.4467 0.05631 0.05134 0.0072 0.0201 1.0000
17.000 1.4416 0.05998 0.05516 0.0066 0.0200 1.0000
17.250 1.4341 0.06420 0.05955 0.0054 0.0198 1.0000
17.500 1.4242 0.06902 0.06453 0.0037 0.0197 1.0000
17.750 1.4110 0.07461 0.07029 0.0014 0.0196 1.0000
18.000 1.3939 0.08120 0.07705 -0.0018 0.0195 1.0000
18.250 1.3717 0.08914 0.08519 -0.0061 0.0194 1.0000
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