RAF 33 AIRFOIL (raf33-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 33 AIRFOIL (raf33-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.39 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf33-il-1000000-n5.txt Download as CSV file: xf-raf33-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAF 33 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8592 0.02822 0.02418 -0.0472 0.6515 0.0202
-11.250 -0.8476 0.02659 0.02233 -0.0453 0.6458 0.0203
-10.750 -0.8144 0.02443 0.01983 -0.0423 0.6365 0.0206
-10.500 -0.8034 0.02266 0.01782 -0.0401 0.6318 0.0209
-10.250 -0.7847 0.02179 0.01683 -0.0387 0.6267 0.0211
-10.000 -0.7623 0.02139 0.01637 -0.0378 0.6224 0.0213
-9.750 -0.7404 0.02084 0.01575 -0.0368 0.6182 0.0215
-9.500 -0.7177 0.02040 0.01523 -0.0359 0.6141 0.0217
-9.250 -0.6961 0.01975 0.01446 -0.0348 0.6099 0.0219
-9.000 -0.6737 0.01918 0.01379 -0.0339 0.6059 0.0220
-8.750 -0.6514 0.01851 0.01301 -0.0329 0.6021 0.0222
-8.500 -0.6281 0.01799 0.01240 -0.0321 0.5982 0.0224
-8.250 -0.6044 0.01751 0.01182 -0.0312 0.5945 0.0227
-8.000 -0.5809 0.01697 0.01115 -0.0304 0.5910 0.0230
-7.750 -0.5569 0.01641 0.01050 -0.0297 0.5878 0.0232
-7.500 -0.5329 0.01583 0.00981 -0.0289 0.5840 0.0234
-7.250 -0.5084 0.01531 0.00918 -0.0282 0.5803 0.0236
-7.000 -0.4836 0.01483 0.00859 -0.0275 0.5767 0.0238
-6.750 -0.4584 0.01438 0.00806 -0.0269 0.5737 0.0240
-6.500 -0.4329 0.01397 0.00757 -0.0264 0.5706 0.0242
-6.250 -0.4070 0.01361 0.00713 -0.0259 0.5670 0.0244
-6.000 -0.3811 0.01326 0.00671 -0.0254 0.5631 0.0246
-5.750 -0.3551 0.01295 0.00632 -0.0249 0.5599 0.0247
-5.500 -0.3292 0.01256 0.00587 -0.0244 0.5569 0.0249
-5.250 -0.3036 0.01207 0.00533 -0.0239 0.5538 0.0254
-5.000 -0.2774 0.01177 0.00500 -0.0235 0.5502 0.0258
-4.750 -0.2509 0.01151 0.00470 -0.0231 0.5467 0.0261
-4.500 -0.2245 0.01129 0.00444 -0.0227 0.5434 0.0264
-4.250 -0.1977 0.01107 0.00419 -0.0223 0.5404 0.0266
-4.000 -0.1710 0.01085 0.00395 -0.0220 0.5371 0.0270
-3.750 -0.1442 0.01066 0.00372 -0.0216 0.5336 0.0273
-3.500 -0.1176 0.01047 0.00350 -0.0212 0.5302 0.0276
-3.000 -0.0641 0.01013 0.00311 -0.0205 0.5237 0.0284
-2.750 -0.0372 0.00997 0.00293 -0.0202 0.5204 0.0287
-2.500 -0.0104 0.00983 0.00276 -0.0199 0.5170 0.0290
-2.250 0.0164 0.00971 0.00262 -0.0195 0.5133 0.0294
-2.000 0.0432 0.00960 0.00248 -0.0192 0.5099 0.0298
-1.750 0.0698 0.00942 0.00230 -0.0188 0.5069 0.0305
-1.500 0.0967 0.00930 0.00219 -0.0185 0.5033 0.0316
-1.250 0.1235 0.00921 0.00209 -0.0182 0.4995 0.0324
-1.000 0.1502 0.00914 0.00200 -0.0179 0.4958 0.0334
-0.750 0.1772 0.00907 0.00192 -0.0176 0.4928 0.0342
-0.500 0.2042 0.00900 0.00185 -0.0173 0.4892 0.0351
-0.250 0.2310 0.00892 0.00178 -0.0170 0.4852 0.0368
0.000 0.2576 0.00887 0.00173 -0.0167 0.4813 0.0393
0.250 0.2844 0.00883 0.00169 -0.0164 0.4777 0.0422
0.500 0.3112 0.00876 0.00166 -0.0161 0.4740 0.0473
0.750 0.3380 0.00872 0.00163 -0.0159 0.4699 0.0538
1.000 0.3643 0.00868 0.00162 -0.0155 0.4656 0.0658
1.250 0.3905 0.00862 0.00162 -0.0152 0.4616 0.0850
1.500 0.4169 0.00856 0.00162 -0.0148 0.4564 0.1048
1.750 0.4428 0.00854 0.00163 -0.0144 0.4500 0.1280
2.000 0.4683 0.00846 0.00166 -0.0140 0.4443 0.1694
2.250 0.4934 0.00836 0.00170 -0.0135 0.4391 0.2316
2.500 0.5169 0.00820 0.00175 -0.0127 0.4341 0.3227
2.750 0.5051 0.00660 0.00171 -0.0043 0.4312 0.8587
3.250 0.6441 0.00700 0.00227 -0.0226 0.4165 0.9577
3.500 0.6750 0.00716 0.00241 -0.0232 0.4112 0.9633
3.750 0.7085 0.00733 0.00254 -0.0245 0.4040 0.9660
4.000 0.7383 0.00746 0.00265 -0.0250 0.3983 0.9687
4.250 0.7639 0.00763 0.00279 -0.0245 0.3924 0.9735
4.500 0.7987 0.00779 0.00292 -0.0262 0.3851 0.9746
4.750 0.8313 0.00798 0.00305 -0.0275 0.3731 0.9757
5.000 0.8614 0.00811 0.00316 -0.0281 0.3654 0.9767
5.250 0.8898 0.00830 0.00330 -0.0285 0.3549 0.9778
5.500 0.9178 0.00848 0.00344 -0.0288 0.3439 0.9791
5.750 0.9446 0.00866 0.00359 -0.0288 0.3353 0.9808
6.000 0.9671 0.00888 0.00378 -0.0279 0.3262 0.9832
6.250 0.9948 0.00907 0.00395 -0.0282 0.3164 0.9842
6.500 1.0244 0.00933 0.00415 -0.0289 0.3034 0.9848
6.750 1.0538 0.00957 0.00435 -0.0297 0.2934 0.9855
7.000 1.0829 0.00981 0.00456 -0.0304 0.2827 0.9864
7.250 1.1105 0.01016 0.00485 -0.0309 0.2668 0.9874
7.500 1.1366 0.01061 0.00519 -0.0312 0.2472 0.9886
7.750 1.1620 0.01105 0.00555 -0.0314 0.2295 0.9900
8.000 1.1873 0.01144 0.00588 -0.0314 0.2175 0.9914
8.250 1.2108 0.01190 0.00628 -0.0312 0.2036 0.9929
8.500 1.2347 0.01233 0.00666 -0.0311 0.1919 0.9940
8.750 1.2603 0.01291 0.00715 -0.0317 0.1725 0.9949
9.000 1.2837 0.01366 0.00777 -0.0320 0.1493 0.9962
9.250 1.2941 0.01571 0.00943 -0.0315 0.0837 0.9989
9.500 1.3170 0.01645 0.01015 -0.0319 0.0744 1.0000
9.750 1.3226 0.01711 0.01081 -0.0287 0.0687 1.0000
10.000 1.3137 0.01784 0.01158 -0.0231 0.0657 1.0000
10.250 1.3112 0.01886 0.01264 -0.0197 0.0623 1.0000
10.500 1.3098 0.02018 0.01396 -0.0168 0.0555 1.0000
10.750 1.3115 0.02151 0.01529 -0.0146 0.0489 1.0000
11.000 1.3116 0.02309 0.01685 -0.0125 0.0413 1.0000
11.250 1.3092 0.02497 0.01869 -0.0105 0.0316 1.0000
11.500 1.3072 0.02695 0.02065 -0.0088 0.0236 1.0000
11.750 1.3070 0.02888 0.02259 -0.0073 0.0189 1.0000
12.000 1.3100 0.03061 0.02434 -0.0061 0.0170 1.0000
12.250 1.3127 0.03240 0.02618 -0.0050 0.0155 1.0000
12.500 1.3156 0.03423 0.02804 -0.0040 0.0146 1.0000
12.750 1.3182 0.03611 0.02997 -0.0030 0.0137 1.0000
13.000 1.3219 0.03793 0.03185 -0.0022 0.0133 1.0000
13.250 1.3248 0.03985 0.03381 -0.0014 0.0126 1.0000
13.500 1.3266 0.04196 0.03597 -0.0007 0.0120 1.0000
13.750 1.3279 0.04421 0.03827 -0.0001 0.0115 1.0000
14.000 1.3294 0.04649 0.04060 0.0004 0.0110 1.0000
14.250 1.3316 0.04875 0.04292 0.0008 0.0107 1.0000
14.500 1.3340 0.05105 0.04528 0.0011 0.0105 1.0000
14.750 1.3363 0.05338 0.04766 0.0013 0.0102 1.0000
15.000 1.3379 0.05583 0.05016 0.0015 0.0098 1.0000
15.250 1.3377 0.05854 0.05293 0.0016 0.0094 1.0000
15.500 1.3385 0.06118 0.05563 0.0017 0.0094 1.0000
15.750 1.3373 0.06408 0.05859 0.0016 0.0089 1.0000
16.000 1.3351 0.06716 0.06173 0.0015 0.0086 1.0000
16.250 1.3327 0.07030 0.06493 0.0013 0.0084 1.0000
16.500 1.3318 0.07333 0.06803 0.0011 0.0083 1.0000
16.750 1.3310 0.07635 0.07111 0.0008 0.0082 1.0000
17.000 1.3290 0.07956 0.07439 0.0004 0.0080 1.0000
17.250 1.3281 0.08266 0.07756 0.0000 0.0077 1.0000
17.500 1.3251 0.08608 0.08105 -0.0005 0.0077 1.0000
17.750 1.3224 0.08951 0.08455 -0.0011 0.0076 1.0000
18.000 1.3191 0.09304 0.08816 -0.0017 0.0074 1.0000
18.250 1.3152 0.09669 0.09186 -0.0025 0.0072 1.0000
18.500 1.3113 0.10040 0.09564 -0.0033 0.0071 1.0000
18.750 1.3082 0.10401 0.09931 -0.0041 0.0069 1.0000
19.000 1.3033 0.10789 0.10326 -0.0051 0.0068 1.0000
19.250 1.2979 0.11191 0.10734 -0.0062 0.0067 1.0000
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