RAF 33 AIRFOIL (raf33-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAF 33 AIRFOIL (raf33-il) Reynolds number: 500,000 Max Cl/Cd: 99.17 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-raf33-il-500000-n5.txt Download as CSV file: xf-raf33-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3184 0.10321 0.09958 -0.0307 0.6570 0.0189
-10.750 -0.3191 0.09903 0.09540 -0.0326 0.6532 0.0195
-10.500 -0.3419 0.09049 0.08687 -0.0366 0.6513 0.0207
-10.250 -0.3380 0.08782 0.08420 -0.0378 0.6469 0.0209
-10.000 -0.3291 0.08618 0.08253 -0.0384 0.6423 0.0211
-9.750 -0.3265 0.08337 0.07973 -0.0396 0.6384 0.0213
-9.500 -0.3275 0.08004 0.07641 -0.0410 0.6349 0.0215
-9.250 -0.3328 0.07632 0.07270 -0.0428 0.6309 0.0217
-9.000 -0.3439 0.07239 0.06878 -0.0451 0.6270 0.0219
-8.500 -0.5496 0.03158 0.02674 -0.0417 0.6288 0.0248
-8.250 -0.5443 0.02863 0.02346 -0.0392 0.6251 0.0251
-8.000 -0.5291 0.02707 0.02170 -0.0376 0.6214 0.0253
-7.750 -0.5086 0.02633 0.02087 -0.0366 0.6170 0.0256
-7.500 -0.4888 0.02540 0.01980 -0.0354 0.6130 0.0259
-7.250 -0.4700 0.02420 0.01839 -0.0341 0.6095 0.0262
-7.000 -0.4507 0.02295 0.01692 -0.0328 0.6062 0.0266
-6.750 -0.4309 0.02159 0.01533 -0.0315 0.6024 0.0269
-6.500 -0.4096 0.02047 0.01399 -0.0304 0.5985 0.0273
-6.250 -0.3874 0.01944 0.01274 -0.0294 0.5948 0.0276
-6.000 -0.3643 0.01852 0.01161 -0.0285 0.5916 0.0280
-5.750 -0.3401 0.01769 0.01062 -0.0277 0.5883 0.0283
-5.500 -0.3152 0.01696 0.00973 -0.0271 0.5846 0.0287
-5.250 -0.2897 0.01641 0.00904 -0.0266 0.5808 0.0291
-5.000 -0.2640 0.01594 0.00844 -0.0260 0.5773 0.0295
-4.750 -0.2381 0.01541 0.00778 -0.0256 0.5743 0.0297
-4.500 -0.2122 0.01468 0.00698 -0.0252 0.5709 0.0302
-4.250 -0.1859 0.01422 0.00647 -0.0248 0.5672 0.0306
-4.000 -0.1596 0.01384 0.00605 -0.0244 0.5636 0.0310
-3.750 -0.1332 0.01352 0.00567 -0.0240 0.5604 0.0314
-3.500 -0.1067 0.01322 0.00532 -0.0237 0.5573 0.0318
-3.250 -0.0800 0.01291 0.00499 -0.0233 0.5537 0.0323
-3.000 -0.0534 0.01263 0.00469 -0.0230 0.5500 0.0329
-2.750 -0.0270 0.01238 0.00438 -0.0226 0.5466 0.0334
-2.500 -0.0007 0.01216 0.00411 -0.0221 0.5434 0.0340
-2.250 0.0259 0.01195 0.00388 -0.0218 0.5402 0.0347
-2.000 0.0527 0.01178 0.00369 -0.0214 0.5366 0.0354
-1.750 0.0785 0.01151 0.00342 -0.0210 0.5331 0.0364
-1.500 0.1047 0.01133 0.00323 -0.0205 0.5297 0.0374
-1.250 0.1309 0.01120 0.00307 -0.0201 0.5263 0.0385
-1.000 0.1576 0.01106 0.00294 -0.0198 0.5229 0.0399
-0.750 0.1841 0.01094 0.00281 -0.0194 0.5193 0.0412
-0.500 0.2105 0.01083 0.00269 -0.0190 0.5155 0.0429
-0.250 0.2365 0.01073 0.00258 -0.0186 0.5120 0.0458
0.000 0.2630 0.01065 0.00251 -0.0182 0.5087 0.0498
0.250 0.2893 0.01054 0.00245 -0.0179 0.5050 0.0565
0.500 0.3155 0.01046 0.00240 -0.0175 0.5011 0.0662
0.750 0.3413 0.01038 0.00237 -0.0170 0.4972 0.0834
1.000 0.3671 0.01031 0.00235 -0.0166 0.4937 0.1055
1.250 0.3930 0.01021 0.00235 -0.0162 0.4898 0.1329
1.500 0.4177 0.01005 0.00237 -0.0156 0.4857 0.1932
1.750 0.4413 0.00985 0.00240 -0.0148 0.4816 0.2818
2.000 0.4414 0.00857 0.00229 -0.0093 0.4785 0.6957
2.500 0.5929 0.00875 0.00309 -0.0294 0.4639 0.9571
2.750 0.6318 0.00897 0.00329 -0.0316 0.4576 0.9651
3.000 0.6653 0.00915 0.00343 -0.0328 0.4522 0.9706
3.250 0.7007 0.00932 0.00356 -0.0345 0.4474 0.9746
3.500 0.7391 0.00944 0.00367 -0.0368 0.4417 0.9773
3.750 0.7717 0.00956 0.00376 -0.0379 0.4358 0.9799
4.000 0.7999 0.00968 0.00385 -0.0381 0.4307 0.9825
4.250 0.8271 0.00977 0.00395 -0.0381 0.4250 0.9841
4.500 0.8573 0.00986 0.00401 -0.0388 0.4187 0.9849
4.750 0.8872 0.00994 0.00409 -0.0395 0.4129 0.9857
5.000 0.9166 0.01004 0.00418 -0.0400 0.4059 0.9867
5.250 0.9454 0.01017 0.00429 -0.0405 0.3986 0.9878
5.500 0.9738 0.01031 0.00442 -0.0409 0.3892 0.9890
5.750 1.0019 0.01047 0.00456 -0.0412 0.3802 0.9903
6.000 1.0291 0.01067 0.00473 -0.0414 0.3703 0.9917
6.250 1.0561 0.01087 0.00492 -0.0416 0.3595 0.9931
6.500 1.0838 0.01107 0.00511 -0.0420 0.3504 0.9942
6.750 1.1124 0.01131 0.00532 -0.0426 0.3400 0.9952
7.000 1.1407 0.01155 0.00554 -0.0432 0.3281 0.9963
7.250 1.1692 0.01179 0.00578 -0.0438 0.3185 0.9976
7.500 1.1972 0.01211 0.00607 -0.0444 0.3066 0.9988
7.750 1.2247 0.01251 0.00642 -0.0450 0.2907 1.0000
8.000 1.2426 0.01298 0.00683 -0.0437 0.2740 1.0000
8.250 1.2591 0.01348 0.00727 -0.0421 0.2582 1.0000
8.500 1.2758 0.01394 0.00770 -0.0406 0.2470 1.0000
8.750 1.2916 0.01444 0.00817 -0.0389 0.2359 1.0000
9.000 1.3050 0.01503 0.00872 -0.0369 0.2219 1.0000
9.250 1.3172 0.01564 0.00930 -0.0347 0.2091 1.0000
9.500 1.3275 0.01629 0.00992 -0.0323 0.1969 1.0000
9.750 1.3348 0.01702 0.01061 -0.0295 0.1849 1.0000
10.000 1.3342 0.01787 0.01142 -0.0254 0.1714 1.0000
10.250 1.3236 0.01889 0.01244 -0.0201 0.1620 1.0000
10.500 1.3089 0.02075 0.01421 -0.0158 0.1388 1.0000
10.750 1.2838 0.02382 0.01706 -0.0117 0.0982 1.0000
11.000 1.2739 0.02624 0.01941 -0.0092 0.0840 1.0000
11.250 1.2706 0.02831 0.02149 -0.0074 0.0759 1.0000
11.500 1.2736 0.02999 0.02321 -0.0061 0.0705 1.0000
11.750 1.2733 0.03199 0.02523 -0.0047 0.0651 1.0000
12.000 1.2768 0.03372 0.02700 -0.0037 0.0606 1.0000
12.250 1.2762 0.03585 0.02914 -0.0025 0.0542 1.0000
12.500 1.2748 0.03811 0.03139 -0.0015 0.0462 1.0000
12.750 1.2722 0.04052 0.03380 -0.0006 0.0385 1.0000
13.000 1.2670 0.04328 0.03653 0.0003 0.0297 1.0000
13.250 1.2630 0.04605 0.03931 0.0009 0.0242 1.0000
13.500 1.2600 0.04884 0.04212 0.0014 0.0208 1.0000
13.750 1.2592 0.05147 0.04480 0.0018 0.0190 1.0000
14.000 1.2585 0.05414 0.04752 0.0021 0.0178 1.0000
14.250 1.2580 0.05685 0.05030 0.0023 0.0166 1.0000
14.500 1.2584 0.05953 0.05305 0.0024 0.0161 1.0000
14.750 1.2579 0.06235 0.05595 0.0024 0.0155 1.0000
15.000 1.2565 0.06532 0.05898 0.0024 0.0149 1.0000
15.250 1.2519 0.06876 0.06249 0.0022 0.0142 1.0000
15.500 1.2500 0.07192 0.06572 0.0020 0.0137 1.0000
15.750 1.2493 0.07496 0.06884 0.0017 0.0134 1.0000
16.000 1.2478 0.07816 0.07212 0.0014 0.0130 1.0000
16.250 1.2451 0.08155 0.07560 0.0010 0.0126 1.0000
16.500 1.2429 0.08491 0.07903 0.0005 0.0124 1.0000
16.750 1.2395 0.08852 0.08272 -0.0001 0.0121 1.0000
17.000 1.2341 0.09240 0.08668 -0.0009 0.0117 1.0000
17.250 1.2299 0.09618 0.09052 -0.0016 0.0113 1.0000
17.500 1.2240 0.10027 0.09470 -0.0026 0.0112 1.0000
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